Note: Descriptions are shown in the official language in which they were submitted.
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DOCKING STATION FOR A ROCKET LAUNCH SYSTEM
BACKGROUND OF THE INVENTION
Field of the Invention
[0002] The present invention relates to a system for delivering various
types of payloads to the
upper atmosphere and beyond, and more particularly to a high cyclic rate
launch rate rocket launcher with
an upper launch station. The cables' self weight is offset by lighter-than-air
balloons. The cables are
tensioned by one or more lighter-than-air balloons and anchored by a pivoting
tether.
Description of the Prior Art
[0005] Many methods of delivering useful materials such as propellants,
gases for life support,
etc. and fabricated items to the upper atmosphere or beyond, exist or have
been proposed in recent
publications.
[0006] These primarily involve rockets powered by chemical, nuclear or
ground based laser or
maser energy sources. Various methods of reducing the cost per unit mass of
delivering useful materials
and fabricated items to the upper atmosphere or beyond, which involve rockets,
exist or have been
proposed.
[0007] These included re-usable rocket powered vehicles such as the soon
to be retired United
States of America's Space Shuttle, or Russia's now inoperative Buran.
Currently, only chemical multi-
stage rockets or vehicles with strap on solid fuel powered rocket boosters, or
rockets such as the USA's
diminutive Pegasus, which is transported to high altitude before launch, are
known to be in service.
[0008] Proposed methods of decreasing the delivery cost to the upper
atmosphere or beyond,
most commonly involve transferring energy to the rockets by increasing either
their initial kinetic or
potential energy before igniting the main motor or motors. Proposals by which
this can be achieved
include: elevation suspended under a disposable, free flight, lighter-than-air
balloon or, forcible ejection
at high velocity from large guns utilizing either chemical propellants or
compressed air or compressed
hydrogen or, transport to high altitude attached to airplanes such as Virgin
Galactic's White Knight Two
or, transport to high altitude towed on a cable tether behind an airplane or,
acceleration to high velocity
using ground based linear induction motors or, jet or rocket powered sleds,
prior to igniting the rocket's
main motor or motors.
100091 One proposed method for reducing the delivery cost, which does not
involve
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rockets, is the so called "Space Elevator" where a large mass is tethered to
the earth by a single
cable many thousands of miles long. The large mass orbits the earth in a
geosynchronous orbit
and keeps the cable taut. This cable would then be used in a manner analogous
to a railway track
on which a train travels.
[0008] The primary difficulty with this latter method is that the tensile
strength of the
material required for the cable far exceeds any existing material, especially
since the self weight
of the cable would be considerable. Another difficulty is to supply the
vehicle climbing this cable
with sufficient energy to essentially climb out of the majority of the earth's
gravitational field. A
weightless, super strong, cable material would be ideal for such a "space
elevator" but, this does
not yet exist. Also, the problem of energy supply up thousands of miles of
cable has prompted the
consideration of beamed microwave or laser power to the climbing vehicle. The
defocusing and
obstructive effect of clouds and the atmosphere on the beamed power is likely
to greatly reduce
the amount of power that actually reaches the climbing vehicle. Dissipation of
energy on the
return of the (climbing) vehicle to the earth is likely to be quite wasteful
because of the need for
braking to prevent it from exceeding the speed capacity of the mechanism
holding the said vehicle
to the cable.
[0009] Many of the current proposed methods require the development of new
materials
or massive structures and are unlikely to see commercial service for many
decades to come, if
ever.
[0010] The majority of current launch methods involve the use of huge
amounts of
energy, derived primarily from fossil fuels such as coal or oil to produce
cryogenic liquid oxygen
oxidizer, cryogenic liquid hydrogen or other liquid hydrocarbon fuels or solid
propellants. This
use of non-renewable resources is inherently inefficient because at each stage
of production of the
fuels there is a compounding of process inefficiencies. As well, the large
mass and sometimes
toxic nature of exhaust material used to propel the vehicle out of the
atmosphere frequently does
ecological damage or may cause climatological disturbances.
[0011] Accordingly, a need exists for a method of delivering useful
materials such as
propellants, gases for life support, etc. and fabricated items to the upper
atmosphere or beyond, at
a cost per unit mass delivered, far less than currently commercially
available, which utilizes
currently available materials and technologies. Furthermore, it would be
ecologically beneficial
to minimize the mass of material used to propel the vehicle out of the earth's
atmosphere by the
use of hydroelectric, geothermal or solar photovoltaic generated electricity
to raise the vehicle as
high as possible before igniting the vehicle's engine or engines.
[0012] Atmospheric monitoring has been in effect for over fifty years.
Measurement of
solar radiation, concentrations of trace gases, temperature, pressure and
other parameters, by
=
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which the direction of the earth's climatological changes can be predicted,
has greatly increased
our understanding of our world's climate. It is of particular importance with
regards to the ozone
hole, the continuous rise of carbon dioxide and other "greenhouse" gases in
the atmosphere, and
now, the more than fifty chemical species in the earth's atmosphere.
[0013] As increased levels of "greenhouse" and ozone depleting gases occur,
such as
carbon dioxide, chlorofluorocarbons, nitrous oxide and sulfur hexafltioride,
which cause global
warming and other changes in the global weather, there arises an increased
requirement for
atmospheric monitoring on a more continuous basis. Current methods for
monitoring atmospheric
conditions involve heavily instrumented aircraft, manned and unmanned; free
flight balloons with
suspended instrument packages; rockets with sampling and instrument payloads;
and ground
based laser and radar stations.
[0014] These, with the exception of the ground based stations, cannot
provide more than a
relatively brief period of atmospheric data sampling. The longest duration of
monitoring by non-
ground based methods currently does not exceed more than a few days in the
case of balloons,
and the shortest, such as rockets, might be measured in minutes. Many of these
methods of
atmospheric monitoring also utilize single use instrument packages, while
existing ground based
stations cannot obtain physical samples to determine the chemical composition,
the bacterial/viral
content, or the intensity and spectral analysis of sunlight and other data
throughout the depth of
the atmosphere.
[0015] Thus, there exists a need for constructions extending from the
surface of the earth
to a great height, on which instrumentation for continuous monitoring and
sampling of the
atmosphere and, incident solar and other radiation may be mounted.
[0016] Radio telecommunications and over the horizon radar are being more
extensively
used for security reasons by many countries throughout the world.
[0017] The recent worldwide security concems about surprise terrorist
attacks has driven
countries such as the United States of America to increase the level of
surveillance by the use of
radar and other means of detection utilizing various regions of the
electromagnetic spectrum.
This is evidenced by the 9/11 Commission Act of 2007 of Congress, relating in
part to the
interoperable radio telecommunication system for the security of the United
States. The range of
ground based radar is limited by the curvature of the earth's surface and, in
an attempt to achieve
greater useful ranges, radar and other systems have been mounted on high
flying aircraft or low
altitude tethered balloons.
[0018] In a similar way, cellular radio telephony operators are currently
seeking to enlarge
the area serviced by the use of high altitude aircraft, with receivers and
transmitters, proposed to
fly in closed circuits over the service area. The extreme high altitude cases
of this are the
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INMARSAT and IRIDIUM satellite phone systems which utilize extremely expensive
and
unrepairable geostationary satellites for telecommunications.
[0019] Thus it may be seen that there is a need for lower cost, high
altitude radar and radio
telecommunications platforms.
[0020] The present invention also relates to tourism. The visitation of
tall monuments such
as the Eiffel Tower, tall buildings such as the Empire State Building, or high
altitude natural
features such as Mount Everest continues to be a commOn activity of tourists.
Indeed, recently
there has also been increasing non-military interest in expensive high
altitude airplane flights.
The recent "X Prize" for safe flight to 100 kilometers or higher won by Burt
Rutan's Space Ship
One is further driving the commercialization of high altitude transport. A
problem with Space
Ship One and Space Ship Two is that their rocket motors uses a liquified
nitrous oxide oxidiser
and hydroxyl terminated polybutadiene solid fuel, which solid fuel produces an
exhaust which
includes soot, partially burnt rubber and other noxious materials. In recent
publications, it has
been stated that alternative fuels for Space Ship Two are being investigated,
asphalt and paraffin.
It is likely that, although these are cheap fossil fuels, combustion will not
be complete. Yielding
polluting exhaust products, in the case of asphalt, metal oxides and acidic
sulphur compounds are
likely. The effect of the soot alone, recently calculated for 1,000 launches
per year by Martin
Ross of the Aerospace Corporation, suggests stratospheric disruption and
soaring temperatures at
the earth's poles. The launch rate published being only a few times per week.
[0021] There is therefore a growing market for less expensive more frequent
transport of
tourists to ever higher altitudes.
[0022] In the past few years, skydiving as a sport has changed to include
ram air wing
type parachutes, the use of auxiliary equipment such as small rigid wings,
miniature surfboards,
rockets and even miniature turbojet engines. Further, the altitude from which
skydivers have been
jumping from has been on the increase, although this has been limited by two
major factors.
These are the limited capability of civilian fixed wing airplanes and
helicopters to operate at
higher altitudes where there exists a civil aviation half hour limit for
oxygen enriched breathing
systems or, a requirement for a pressurized suit or cabin. In the short term,
it is expected that
civilian pressurized suits will become available to skydiving enthusiasts as
the market for high
altitude skydiving develops.
[0023] Even more extreme forms of sky diving are even now being considered.
These
proposed forms involve jumping from the upper reaches of the atmosphere or
even re-entry from
space, as might occur when occupants of distressed orbital spacecraft are to
be returned safely to
earth.
[0024] Thus, there is an increasing market for novel, and higher altitude
platforms for the
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various new forms of skydiving. Indeed, there is also a continuing demand for
low cost platforms
at altitudes of up to ten thousand feet.
[0025] In recent times, the rapid deployment of aircraft to sites of
military interest has
become practically a necessity, for reconnaissance or other purposes.
Additionally, there is a
growing interest in commercial hypersonic transport. Towards this end,
hypersonic aircraft with
supersonic combustion engines are being developed in many countries to fulfil
these perceived
needs.
[0026] However, the engines of such aircraft, designed to operate
efficiently at higher
Mach numbers have been reported to require the attainment of a velocity in
excess of three times
the speed of sound for them to start. Considerable complexity, with a
concomitant weight penalty
is required for an engine to operate in the various flight regimes from
stationary to hypersonic.
Apart from using rocket boosters to achieving starting speed, the other design
path appears to
require a two part engine. The first part is a turbofan or turbojet engine
which predominates in the
flight regime from subsonic to low Mach number supersonic, transitioning to
the supersonic
combustion engine at high Mach numbers, and shutting down the first part.
[0027] Engines designed to operate in the hypersonic range only, many with
no moving
parts, would therefore be lighter in weight, simpler in construction, and
hence less expensive.
[0028] In 2003, the manned space shuttle Columbia of the United States of
America was
destroyed upon re-entry into the earth's atmosphere, due to structural damage
which occurred
during the launch phase. As well, over time, there has also been an
accumulation of orbital craft
in need of repair; and distressed orbital craft, and objectionable and
dangerous debris which needs
to be removed from orbit.
[0029] Since craft such as the Columbia space shuttle of the United States
are heavy, and
they lack main engines that can operate for significant lengths of time after
re-entry due to the
hazards and weight penalties of carrying cryogenic or other fuels for use on
the return flight in
atmosphere, these craft must leave orbit at specific points if they are to be
able to glide to the few
airports with runways of sufficient strength and length which exist close to
its orbital track.
[0030] Thus, it is inevitable that others will create smaller craft capable
of performing
useful work outside the atmosphere, with the capability of flying under their
own power in
subsonic, supersonic or sustained hypersonic flight in the earth's atmosphere.
These are likely to
be launched using rocket power and, after re-entry at any point, fly to any of
the multitude of
existing civilian or military airfields suitable for such smaller aircraft
and, land safely.
[0031] These will be used for the quick, safe retrieval of passengers of
damaged orbital
craft and, repair or removal from orbit of distressed unmanned orbital craft,
and objectionable and
dangerous debris. Another type, soon to come into service, is a small service
vehicle for refuelling
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or attaching to distressed space craft and acting as a tug to extend the
useful life of such vehicles.
Further small craft or rockets can be used to launch small satellites, or
modular components for
the assembly and fuelling of large constructions in orbit which may be used to
escape the earth's
gravitational field to possibly deflect dangerous asteroids, or explore the
solar system. The
European Space Agency and Russian equivalent Roscosmos have recently begun to
consider the
creation of a shipyard in low earth obit to facilitate moon or mars missions
utilizing the yet to be
built cargo return advanced re-entry vehicle (ARV).
[0032] Additionally, it is expected that there will be a continuing need to
service satellites
and, other orbital craft. This servicing could include delivering food, fuel,
compressed or liquefied
gases for breathing or other uses, medical and scientific supplies,
electrical, mechanical or other
equipment to replace or upgrade spacecraft systems, transporting sick or
injured personnel, or
replacing personnel.
[0033] Thus, there is expected to be a need for a quick, inexpensive means
of launching
modular components for assembly and fuelling in space, small utility craft,
small satellites and
other devices.
[0034] The sensitivity of many telescopes used in astronomy has been
greatly degraded
due to atmospheric dust and aerosols as light is reflected or scattered by the
aforementioned
particles. The least affected telescopes are generally to be found at the top
of remote mountains,
above much of the atmosphere where most of the dust and aerosols are to be
found.
[0035] Thus, there is a further need for high altitude platforms on which
sensitive
telescopes may be mounted. Particularly, multiple platforms and telescopes may
be used to
simulate an extremely large aperture telescope as currently used to locate
planets in other solar
systems.
[0036] As the Indonesian tsunami disaster unfolded in December 2004, it was
clear that
reconnaissance of many of the affected areas and subsequent delivery of
initial relief supplies did
not occur until days or even weeks after the event, with the consequence that
many tens of
thousands died, more than if early relief had been available. Thus, there is a
need for a fast
suborbital rocket launching system to deliver numerous small unmanned
reconnaissance drones
and thousands of tons of terminally GPS guided parachute delivered relief
supplies using simple
GPS-guided disposable rockets.
BRIEF SUMMARY OF ME INVENTION
[0037] Accordingly, a need exists for a method of delivering useful
materials such as
propellants, gases for life support, etc. and fabricated items to the upper
atmosphere or beyond, at
a cost per unit mass delivered that is far less than current1S, commercially
available, which utilizes
currently available materials and technologies. Furthermore, it would be
ecologically beneficial
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to minimize the mass of material used to propel the vehicle out of the earth's
atmosphere by the
use of hydroelectric, geothermal or solar photovoltaic generated electricity
or other renewable
source of energy to raise the vehicle as high as possible before igniting the
vehicle's engine or
engines.
[0038] An object of the present invention is to provide a high launch rate
rocket launcher
for sending payloads to space, as well as to satellites located in space.
[0039] Still another object of the present invention is to provide a high
launch rate rocket
launcher which may utilize hydroelectricity or other renewable energy for
elevating the rocket to
launch altitude.
[0040] It is another object to utilize a more environmentally friendly fuel
and oxidizer
made using alternative or renewable energy.
[0041] Yet another object of the present invention is to provide an upper
pivoting launch
station utilizing electrically powered tubular launch carriages, the launch
station being connected
to the ground by cables to which are attached lighter-than-air balloons for
tensioning and
supporting the cables and associated structures.
[0042] A further object of the present invention is to provide a means for
recovering
potential energy involved in returning empty rocket launching carriages, after
launch, to the earth,
via tethers, through the use of regenerative braking utilizing motor
generators, for re-use.
[0043] Yet another object of the present invention is to provide
atmospheric monitoring
on a more continuous basis as increased levels of "greenhouse" gases or other
pollutants in the
atmosphere cause changes in global weather.
[0044] A further object of the present invention is to provide high
altitude radar and radio
telecommunications platforms to greatly increase the spatial volume and area
of earth's surface
respectively covered.
[0045] Another object of the present invention is to provide continuous,
reasonably priced
commercial access for tourists to visit levels of the atmosphere inaccessible
by other means
except for rockets, aeroplanes or free flying lighter-than-air aircrafts.
[0046] Still yet another object of the present invention is to provide
higher altitude
platforms than are presently available for the various new forms extreme
altitude or space
skydiving, as well as low cost platforms at altitudes up to ten thousand feet
which can be accessed
without supplementary oxygen or a pressure suit.
[0047] Another object of the present invention is to provide a quick,
inexpensive means
of launching small utility craft for safe retrieval of passengers of damaged
orbital craft, repair,
upgrade or removal from orbit of distressed unmanned orbital craft and
objectionable and
dangerous debris.
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[0048] Yet another object of the present inventiOn is to
provide high altitude platforms
above the earth's cloud layers on which sensitive telescopes may= be mounted,
especially those
which can combine by computational means, the electromagnetic waves inclusive
of light and
radio waves, received in such a manner as to act as a single telescope of a
diameter equal to the
distance of the outermost members of the array, for superior observations than
are presently
available, except from space.
[0049] A further object is to provide a means for
servicing satellites and other orbital craft,
= for example for supplying food, compressed or liquefied gases for
breathing or other uses, fuel,
medicine and scientific supplies, electrical, mechanical or other equipment to
replace or upgrade
spacecraft systems, and for transporting sick or injured personnel, or
replacing personnel.
[0050] It is an object to provide a transporting system
for transporting rocket-loaded
carriages along cables extending up through the atmosphere to a launch
station.
[0051] It is a further object for providing carriages for
carrying rockets along cables to a
launch station located high in the atmosphere.
[0052] It is yet an additional object to provide an
apparatus for holding and directing
rocket-loaded carriages to the apparatus for conveying the carriages along the
cables to a launch
station located high in the atmosphere, and for conveying empty carriages from
the launch station
to the ground.
[0053] Yet a further object is to provide a system for
safely storing rockets, and for
delivering the rockets or rocket-loaded carriages to the apparatus for holding
and directing the
rockets or rocket-loaded carriages to the apparatus for conveying the rockets
or rocket loaded
carriages to a launch station located high in the atmosphere.
[0054] The provision of the apparatus for conveying rocket-
loaded carriages is also an
object of the invention.
[0055] Another object of the invention is a system for
conveying rockets, components of
rockets, carriages for rockets and/or holders of conveying devices for rockets
from a storage
facility to a holding and assembly facility, for subsequent transport to the
apparatus for raising the
rocket-loaded carriage to a launch station.
[0056] It is a further object of the present invention to
provide a transverse loader for
loading rockets into carriages.
[0057] An additional object is the provision of-an
elevating assembly for elevating a
rocket-loaded carriage to the apparatus for loading the rocket-loaded carriage
into a set of
elevated cables to a rocket launch station.
[0058] It is an additional object to provide a turret for
receiving a rocket-loaded carriage,
and related apparatus for orienting a rocket-loaded carriage to a=guide
structure apparatus for
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disposing the rocket-loaded carriage on the cables directed to the launching
station.
[0059] It is still a further object of the invention for providing devices
for connecting
lighter-than-air balloons to a cable system to stably hold and separate the
cables which are
directed to the launching station.
[0060] Another object of the invention is to provide a docking station for
docking a
rocket-loaded carriage on a set of cables going to the launching station.
[0061] The object of providing electrical power for transporting a rocket-
loaded carriage
along a cable system to the elevated launching station is another goal of the
present invention.
[0062] Another object of the present invention is to provide a lift ring
for lifting a rocket-
loaded carriage along the cable system above the docking station.
[0063] An additional object is the provision of a device for separating
cables from the
ground to an elevated launching station, and for stabilizing the cables.
[0064] It is also an object of the present invention to provide connecting
apparatus for
attaching frames and other apparatus to cables extending between the ground
and an elevated
launching station.
[0065] The provision of an apparatus for holding a rocket within a carriage
is also an
object of the present invention.
[0066] Another object is the provision of a telescope mount for use with a
set of cables
held upright in the atmosphere.
[0067] The provision of a rocket to be carried upwardly in a carriage for
holding a person
or persons, or equipment and supplies, is also an object of the present
invention.
[0068] An additional object of the present invention is an improved
hydrostatic pressure
compensating suit to be worn by a person to permit the endurance of high
accelerations during
rocket launch and atmospheric re-entry.
[0069] These objects are achieved according to the preferred embodiments of
the
invention discussed below. Other objects will be apparent to those skilled in
the art from the
inventive concepts as discussed below and from the attached claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0070] Fig. 1 depicts in schematic form some of the features of a preferred
embodiment of
the rocket launch system according to the invention.
[0071] Figs. IA and 1B are detailed views of the features shown in Fig. 1.
[0072] Fig. 2 is a schematic view showing the assembly and basic loading
portion of the
rocket launcher system according to the preferred embodiment of the invention.
[0073] Fig. 3 shows the loading of a rocket into a lateral conveyance
device according to
an aspect of the preferred version of the invention.
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[0074] Fig. 4 is a schematic view showing a different view of a carriage
holding a rocket, a tipping
mechanism and a lateral conveying device.
[0075] Fig. 5 is a schematic view of the plan layout showing a tracked loop
for carriages, storage racks,
rocket holding and assembly stations, carriages, fuel storage apparatus and an
electrical supply system
relating to readying rockets for launching pursuant to the preferred
embodiment of the invention.
[0076] Fig. 5A is an enlarged detail of a portion of tracks illustrated in
FIG. 5.
[0077] Fig. 6 shows in schematic form, the loading of a rocket into a fuelling
or assembly bay according to
a preferred embodiment of the invention.
[0078] Fig. 7 shows a detail of a transverse loader as shown in FIG. 6.
[0079] Fig. 7A is an enlarged detail perspective drawing of a leg and twist
lock pin shown in FIG. 7.
[0080] Fig. 8 is a schematic view showing the operation of an elevating
assembly of the preferred
embodiment of the invention with a lateral conveying device, and a rocket
holding carriage.
[0081] Fig. 8A is an enlarged detail view of one version of apparatus for
supporting a turntable for
rotation.
[0082] Fig. 8B is an enlarged detail view of another version of apparatus for
supporting turntable 72 for
rotation.
[0082a] Fig. 8C is a view of turntable support apparatus.
[0083] Fig. 9 is a schematic view of an elevating assembly, a rotating bed, a
lateral conveying device, a
portion of a carriage according to a preferred embodiment of the invention.
[0084] Fig. 9A is an enlarged perspective view of a tapered, alignment pin.
[0085] Fig. 9B is an enlarged perspective view of a fractional twist lock pin.
[0086] Fig. 9C is an enlarged detail view of the base of a carriage.
[0087] Fig. 10 shows the apparatus for receiving, aligning and commencing the
insertion of a rocket
holding carriage into the cableway according to the preferred embodiment of
the invention.
[0088] Fig. 10A is an enlarged detail view of a cable spacer.
[0089] Fig. 11 shows a further portion of the preferred part of the invention
with respect to the cable
system for transporting rocket holding carriages.
[0090] Fig. 12 is a detail of the upper portion of the preferred form of the
invention in schematic form
showing a balloon assembly for elevating a cable assembly and parts disposed
thereon according to a
preferred aspect of the present invention for lifting the rocket holding
carriage.
[0091] Fig. 13 is a schematic view of an upper part of a preferred part of the
present
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invention showing a portion of the cable assembly, and different components
attached thereto.
[0092] Fig. 13A is an end view of a carriage with an end cover in the open
position.
[0093] Fig. 13B is a perspective view of an end of the carriage for use in
the apparatus
shown in Fig. 13, and Fig. 13C is a side, partly cross-sectional view of the
carriage showing
operating positions of some of its components.
[0094] Fig. 14 is a schematic cross-sectional view of the preferred
embodiment of the
invention showing a cable assembly and different parts attached thereto.
[0095] Fig. 14A is an enlarged detail view of part of a carriage end
gripper.
[0096] Fig. 15 is a schematic view of a preferred embodiment of the
invention showing a
stabilizing portion for the balloons and the cable assembly.
[0097] Fig. 15A is a detailed view of a portion of the stabilizing portion
for the balloons
shown in Fig. 15.
[0098] Fig. 15B is an exploded perspective view of the connection of an
upper spacer to a
cable, and Fig. 15C is a plan view thereof.
[0099] Fig. 15D is an enlarged perspective view of cable attaching
structure for the middle
of a spacing assembly arm.
[00100] Fig. 15E is an exploded perspective view of the connection of a
lower spacer to a
cable and to a large harness.
[00101] Fig. 16 is a detailed schematic plan view of part of the
stabilizing portion of the
preferred form invention, taken in the direction 16-16 in Fig. 15.
[00102] Fig. 17 is another detailed view of part of the stabilizing part of
the preferred
embodiment of the invention, taken in the direction 17-17 in Fig. 15, showing
certain force
vectors.
[00103] Fig. 18 is a perspective schematic view of a stabilizing assembly
with thrusters
according to the preferred embodiment of the invention.
[00104] Fig. 19 is a perspective view of a cable stabilizing device
according to a preferred
form of the invention.
[00105] Figs. 20A and 20B are side views of two of many sets of lighter-
than-air balloons
attached to a cable assembly according to preferred forms of the invention.
[00106] Fig. 21 is a perspective view of a multistranded cable as may be
used in the
cableway of the launch system, according to preferred form of the invention.
[00107] Fig. 22 shows the construction for mounting items to the side of a
cable as shown
in Fig. 21.
[00108] Figs. 23 and 24 are cross-sectional views of variations of the
construction shown in
Fig. 22.
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[00109] Fig. 25 shows in cross-sectional view the engagement of a cable by
the wheels of a
traction drive for driving up or down said cable, according to a preferred
form of the invention.
[00110] Fig. 26 is a perspective view of a retractable arm assembly,
according to a
preferred embodiment of the invention.
[00111] Fig. 27 is a detail showing a retractable arm assembly for holding
a rocket in a
carriage according to the preferred embodiment of the invention.
[00112] Fig. 28 is a schematic view of the upper portion of a preferred
embodiment of the
rocket launching invention if a telescope is to be mounted on top of the main
lift balloon or
balloons.
[00113] Fig. 28A is a perspective view of the upper portion of Fig. 28.
[00114] Fig. 28B is a detailed, enlarged detail cross-sectional side view
of a portion of the
apparatus shown in Fig. 28 including a geared rotational drive system and a
ring bearing, and Fig.
28C is taken in the direction 28C-28C in Fig. 28B, and showing generally how
cables may be
terminated.
[00115] Fig. 29 shows a possible telescope mount for use in the embodiment
shown in Fig.
28, the view being in a detailed, perspective form.
[00116] Fig. 30 is a schematic view of a rocket for launching a single
space suited person,
according to a preferred embodiment of the invention.
[00117] Fig. 31 is a variant of the rocket for multiple, individually
releasable pods or space
suited persons.
[00118] Fig. 32 shows a space suited person on a detachable re-entry frame
utilizing an
aero-spike for shocicwave initiation.
[00119] Fig. 33 shows another variant of a detachable re-entry frame
utilizing an aero-spike
for shockwave initiation.
[00120] Fig. 34 is a schematic of a space suit to be worn by an occupant
according to a
preferred embodiment of the invention for use in exiting and re-entering the
atmosphere.
[00121] Fig. 34A is a detail of the space suit helmet shown in Fig. 34, and
Fig. 34B is a
further detail of the space suit helmet of Fig. 34.
[00122] Fig. 35 shows an apparatus for one method of varying the internal
volume of a
space suit shown in Fig. 34.
[00123] Fig. 36 is a detailed view of a person's limb within a portion of
the space suit of
Fig. 34.
[00124] Figs. 37 and 38 show re-entry capable aero space plane versions of
the rocket
assemblies mounted on top of rockets, one with wings extended and one with
wings folded for the
transport within a carriage, according to a preferred embodiment of the
invention.
CA 02875464 2014-12-18
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[00125] Fig. 38A is a pictorial view of a lifting-body type aerospace plane
with folded lift
and control structures for use with a preferred embodiment of the invention.
[001261 Fig. 39 is a schematic view of a satellite or other payload carried
on a rocket
according to part of a preferred embodiment of the invention with
jettisonable, aerodynamic,
protective shells.
[001271 Figs. 40 and 41 show a perspective and a cross-sectional view of a
rod as a type of
cable to be used instead of a wire rope.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS OF THE INVENTION
[00128] The preferred embodiment of the invention is initially described in
general terms
referring to some components described in more detail below. The general
components are shown
in such general terms in Figs. 1, IA and 1B. The preferred embodiment is a
rocket launch system
1 which includes apparatus for moving a rocket 18 to be launched. Rocket 18 is
first either in a
container or rocket-transporting device such as a carriage 20 or is to be
loaded into carriage 20,
from storage racks 7. Carriages 20 have cylindrical length-wise bores into
open-ended, pressure-
and-heat continuous tubes 836 (Figs. 13, 13C) which are disposed and held in
place for receiving
a rocket 18. Carriages 20 are weatherproof and have a longitudinal axis, which
is the same
longitudinal axis of tube 836. Rockets 18, components thereof, and carriages
20 which may or
may not be loaded with rockets 18, are conveyed to storage racks '7 by an
appropriate transport
railing car on a railway 3 to an off loading area 5. A crane 48 carries
respectively rockets 18,
and/or carriage 20 and/or a component of rocket 18 travels or is used to
maintain various parts of
the rocket launch system I on relatively narrow crane tracks 78. Rockets 18
may have fins 21
(Fig. 7), and each carriage 20 has internal supports in addition to tube 836.
[00129] A transverse loader 50 travels on tracks 90 in the directions shown
by arrows A in
Fig. I A, tracks 90 being located further apart from each other than crane
tracks 78. Transverse
loader 50, which is preferentially used to transfer rockets 18, carriages 20,
etc., from storage racks
7 to assembly or fuelling bays 10, includes trucks 92 for travelling on tracks
90, and has a
wheeled truck 98 movable on a pair of transverse, parallel rails 97 on top of
beams 96, and an
elevator assembly 100 attached to a wheeled truck 98. Crane 48, which is
preferentially used to
perform launch system maintenance, may also be used to remove rockets 18,
and/or carriages 20,
etc. from storage racks 7, and transfer rockets 18 and/or carriages 20 to
assembly/fuelling bays 10
(there would usually be a plurality of assembly bays 10). Elevator a.ssembly
100 moves on rails 97
in the direction shown by the arrows B. Carriage 20, which may or may not have
been loaded
with a rocket 18 by one way or another, is placed in assembly bay 10. The
entire operation is
controlled by appropriate control equipment at a local launch control or
systems control bunker
120.
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100130] Referring to Figs. IA and 2, a lateral conveying device 46 carries
carriage 20 with
rocket 18 loaded therein along a set of tracks 17 disposed in below-the-ground
paths 14 and 14A,
which are located between vertical walls 16. Path I4A (also referring to Fig.
5) leads to a closed
loop pathway 15 also having tracks 17. Lateral conveying devices 46 move in
the direction shown
by arrows C. Lateral conveying device 46 transports carriage 20 with rocket 18
to a launcher 119
which includes an elevating assembly 60. Elevating assembly 60, referring to
Figs. 8 and 9,
includes an upper swiveling mechanism 61. Carriage 20 is elevated to an above-
the-ground
turntable mechanism 63. Turntable mechanism 63 includes a turntable base 122
and a turret
assembly 123 (Figs. 8, 10, 11). Turret assembly 123 comprises a turntable 72,
a lower guide tube
124 and a secondary guide structure 125, the latter being operatively
connected to a set of power
and transporting primary cables 27.
[00131] Primary cables 27 are electric energy providers for rocket-loaded
carriages 20
being transported thereon. Electrical energy could be provided by one set of
electricity-
conducting cables, and carriages 20 could be transported by a second set of
set of strong,
transporting cables. However, the electric power lines and the rocket-
transporting lines have been
integrally combined into one of a set of power and transporting primary cables
which function
both as an electrical energy carrier and to support rockets (preferably in
carriages to transport said
carriages to and from high altitudes). Primary cables 27 have a low end
portion at or near
secondary guide structure 125 or turntable mechanism 63 and a high end portion
which when in
use is at high altitudes. Said power and transporting primary cables 27 are
preferably three in
number for carrying three-phase electrical power. Primary cables 27 referring
to Figs. 1, 1B, 11,
12, 13 and 14, are connected to a docking station 166,-from which extend a set
of secondary
cables 184. Cables 184 operatively guide a lift ring assembly 182, which is
adjusted to an
appropriate height above docking station 166 once the pre-selected launch
azimuth angle is
adjusted with carriage 20 engaged by lift ring assembly 182 and an upper ring
part 172 of docking
station 166. After being lifted out of engagement with upper ring part 172 and
released from a
carriage end gripper 196, lift ring assembly 182 is adjusted to the pre-
selected launch elevation
angle. Lift ring assembly 182 is positioned above docking station 166 and
located at significant
altitudes for the final step in the launching of rockets 18 as explained
below.
[00132] Cables 27, 184 and any other cables are supported to the upper
atmosphere by a
series of lighter-than-air balloons 164 and 160, the balloons are composed of
a skin holding a
lighter-than-air gas. Said lighter-than-air balloons 164 are attached to said
primary cables 27
intermittently along the length of said primary cables 27 to support
cumulatively the self weight
of said set of primary cables 27 and any structure carried by said primary
cables 27. Balloons 160
support the otherwise unsupported portion of cables 27, and any structures
attached thereto, and
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ail structures and assemblies from and including docking station 166 up to
said balloons 160, and
tension cables 27 and 184 so that they may carry a useful load. Cables 27 are
separated from each
other by a set of spacer or stabilizer assemblies 158. (Cables have been shown
throughout most
of the description as wire ropes, but they could be rods as explained later.)
(001331
Each assembled rocket 18 within a carriage 20 is transported from an assembly
bay
into lower guide tube 124, then into secondary guide structure 125, and thence
to docking
station 166 by means of traction drives 26 which include an electrically
powered energizing
apparatus 168. Traction drives 26 can comprise a set of traction drive wheels
26A connected to
apparatus for converting electrical power to mechanical power and for
interconnecting together
the mechanical and electrical apparatus. Thus, a set of gears in a gearbox G
can be operatively
connected to electrically powered energizing apparatus 168. The latter can
include a motor-
generator M-G operatively connected to gears in gearbox G as shown in Figs.
9C, 15C and 25.
= Traction drives 26 are built into carriage 20. Carriage 20 travels along
and electrically powered
energizing apparatus 168 derives power from primary cables 27 as when carriage
20 is lifted up
(or climbs) cables 27 and other cables connected to them as described below by
traction drives 26.
The self weight of cables 27 and all iteMs permanently affixed to said cables
are periodically
offset by lighter-than-air balloons 164 and which are held taut by lighter-
than-air balloons= 160.
'Traction drive wheels 26A and electrically powered energizing apparatus 168
(composed of gears
in gearbox G coupled to motor generator M-G) convert electrical energy to
kinetic energy to
energize electrically powered energizing apparatus 168. The latter is
advantageously a reversible
electrically powered energizing apparatus for converting-potential energy to
electric power as
carriage 20 descends, and delivering electric power to the electric power
lines forming part of the
cables upon which carriage 20 is traveling. When carriage 20 requires
electrical energy to ascend,
wheels 26A are driven by motor generator M-G via converting apparatus such as
set of gears in
gearbox G which rotate in response to being energized by motor-generator M-G.
When carriage
descends under the influence of gravity, traction drives 26 act as a
regenerative brake and
operate gears in gearbox G (or any other device for changing rotational speed)
=which drives
motor-generator M-G (or any other device for converting mechanical energy to
electrical energy).
Balloons 160 and 164 preferably have inclined sides such as shown in Figs. 1,
11, 20A and 28;
cylindrical sides as shown in Fig. 20B, or can be spherical or have other
shapes as well. lligh
altitude balloons are well known and are continuously being developed and
improved.
Appropriate balloons 160 and 164 should preferably remain functional in the
applications for the
present invention for many months and optimally for years. Balloons for going
to the stratosphere
have been known and used since the 1950's. Carriage 20 is lifted further along
secondary cables
184 and rotated and then tilted according to predetermined amounts as
discussed below, after
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which rocket 18 is launched.
[00134] The foregoing description provides an overview of components ofa
preferred form
of the invention. Set forth below is a more detailed discussion of the
invention in its preferred
form s.
[001351 Rockets 18 and their respective payloads are assembled, loaded
into carriages 20
and fuelled if required, and kept in blast-resistant assembly bays 10 prior to
launch. Each bay 10
is located below the ground surface and is constructed so as to limit damage
in case there is an
accidental detonation of the propellant of a rocket 18. Each bay 10 has an
inverted surface in the
shape of an inverted frustum 12 referring to Figs. 2 and 11 of a cone made of
an appropriate
reinforced concrete material or the like for limiting the effects of any such
blast by deflecting it
upwardly and laterally. Each bay 10 is connected by means of below-the-ground
paths 14 and
14A to closed loop path 15. Path 14 ends at an inclined open chute 86 (Fig. 6)
with upwardly
sloping wall 16A (Fig. 2) facing into the lateral opening of assembly bay 10.
This deflects any
lateral component of the possible blast from bay 10 upwards and away from the
supporting
apparatus (structures, equipment) for launch system 1, and from personnel.
Path 14 then turns at
approximately 90 degrees to join with path 14A. Each bay 10 is capable of
holding a rocket 18
within a carriage 20. Each rocket 18 can comprise a short duration booster
rocket motor for
ejecting rocket 18 front its open ended continuous tube 836 (Fig. 13A) within
carriage 20 with
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such a velocity that, even if the main rocket engine misfires, the short
duration booster rocket
motor and rocket 18 will not fall and damage rocket launching system 1. The
booster rocket motor
would operate only within the heat and pressure resistant confines of the
container in which it is
held, as described below. Each rocket 18 has one or more main motors for
driving rocket 18 to its
design velocity.
[00136]
Each carriage 20 has opposed end openings 24 (Figs. 9C, 13, 13A), and hinged
weather end covers or retractable membranes 30 (Figs. 9C, 13, 13A) at both
ends thereof to
protect rocket 18 in carriage 20 while carriage 20 travels from ground through
the atmosphere.
These covers 30 can be swung to open both ends of carriage 20 or membranes 30
retracted to
likewise open both ends of carriage 20, as shown in Fig. 13A. Also within
opposed end openings
24 are reversible variable pitch thrusters 31 hinged parallel to one side of
carriage 20 so that they
may be rotated to a position perpendicular to the ends by use of actuators 29
(Figs. 13B, 13C).
Each carriage 20 has multiples of three traction drives 26 (Fig. 9C) equally
spaced around the
periphery of carriage 20 for the purpose of gripping and pulling the carriage
20 up equally spaced
primary power cables 27. Cables 27 and 184 have suitably high tensile
strengths and conductivity,
as discussed below. Traction dries 26 are powered by the foregoing three
equally spaced primary
power cables 27, cables 27 carrying three-phase power from which traction
drives 26 draw their
power. Traction drives 26 are reversible, using electrical power to raise
carriage 20 or generate
electrical power when used as regenerative brakes. Traction drives 26
operating in the
regenerative braking mode convert the potential energy of the carriage 20 as
it is lowered, into
electricity which is fed back to cables 27, which recovered electricity may be
used to assist the
raising of other loaded carriages in adjacent launch systems 1. Traction
drives 386 (Fig. 28) and
26 (Fig. 9C) operate in a similar manner. The interior of can-iage 20 is
designed to be capable of
resisting the heat, and blast effects caused by the operation of the short
duration booster rocket
motor. End covers or membranes 30 (shown in detail in Figs. 9C and 13A)
protect rocket 18 held
in carriage 20 from any adverse weather and may be used to contain inert or
relatively inert gases
within the interior of carriage 20 surrounding rocket 18 such as nitrogen to
inhibit combustion of
any reactive materials escaping from rocket 18 during transport to the high
altitude launching
position. The upper end of carriage 20 may have twist pin lock receptacles 32
(Fig. 13A) similar
to fractional rotation twist pin sockets 154 (Fig. 9) (discussed below) to
receive twist lock pins
204 (Figs. 12 and 13) similar to a fractional rotation twist lock pin 144
(Fig. 9) (also discussed
below) which arc used to lift carriages 20 in preparing for a rocket launching
process as discussed
below.
[001371
Each carriage 20 has internal retractable arms 34 or 35 (Fig. 26, 27) which
hold the
rocket securely within carriage 20 such that centers of gravity 36 and 37
(Fig. 13) of carriage 20
and rocket 18 respectively are stably positioned in the middle of carriage 20
at its center of
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gravity. Small elastomeric or pneumatic wheels 372 (Fig. 27) may be attached
to the periphery of
the rocket to help prevent rubbing contact between the rocket and the inside
of carriage 20 during
ejection if the rocket's thrust vector does not pass exactly through the
rocket's center of gravity.
Retractable arms 35 and associated parts are discussed hereinafter.
[00138] Referring to Figs. 3-6, there are different ways in which rockets
18 could be loaded
in carriages 20. In one version, a rocket 18 is initially assembled
horizontally, inserted into
carriage 20, and initially placed on a wheeled loader 38 (Fig. 3) in the
direction shown by the
arrow D. Carriage 20 is then placed in a hydraulic rotator 39, rotator 39
having a hydraulically or
otherwise rotatable bed 40 mounted between stands 41 for rotation on pins 42
by means such as a
hydraulic actuator 43 (or some other appropriate actuator). The piston rod of
hydraulic actuator 43
is almost entirely retracted inside the cylinder since carriage 20 has just
passed over the piston and
cylinder. Counterweights 44 are designed in each of the four corners of a bed
40, so as to cause
the center of gravity of bed 40 to be co-incident with the axis of rotation of
pins 42 and with the
center of gravity of the rocket 18 and carriage 20 assembly ¨ thereby reducing
the actuation force
which the hydraulic actuator 43 or other means of rotation, has to exert.
Rockets 18 could have 4
previously been placed in horizontally oriented carriage 20 of lateral
conveying devices 46 (or
similar transporters) prior to rotation to a vertical orientation by hydraulic
rotators 39; or rockets
18 could have been placed in upstanding carriages 20 previously situated on
lateral carrying
devices 46 in assembly bays 10 by means of transfer loader 50. Referring to
Fig. 6, transverse
loader 50 or crane 48 can be used to transfer empty carriages 20 onto
prepositioned lateral
conveying devices 46 as explained below, in assembly bays 10, after which
loader 50 or crane 48
would load a rocket 18 into carriage 20.
[001391 Lateral carrying devices 46 are shown in Figs. 1-6, 8, 9 and 10.
Lateral carrying
devices 46 travel along paths 14, 14A and pathway 15 on tracks 17. Pathway 15
forms a closed
loop which passes under above-the-ground turntable mechanism 63 (Figs. 1A, 8,
10, 11 discussed
below) and carry carriages 20 each loaded with a rocket 18 from blast
resistant assembly bays 10
to elevating assembly 60 as shown in Figs. 2 and 8, and carry empty carriages
20 as well. Each
lateral conveying device 46 has a platform 54 (Fig. 9) with a generally
triangular recess 56 (Fig.
2, 4) for receiving the end of a carriage 20 so that carriage 20 is in an
upright position, with the
outer edges of carriage 20 fitting into recess 56. Lateral carrying device 46
is shown having
independently steerable wheels 58 (Fig. 9) for moving lateral conveying device
46 on tracks 17,
and further has an appropriate steering mechanism to enable lateral conveying
device 46 to travel
along paths 14 and 14A, and pathway 15. An appropriate locking mechanism,
which may include
tapered alignment pins 142 (Fig. 9, discussed below), and fractional rotation
twist lock pins 144
(Fig. 9, discussed below), is provided for locking carriage 20 in recess 56 on
platform 54. Lateral
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conveying devices 46 further have similar receptacles as found on the bottom
of carriages 20 to
receive alignment pins and fractional rotation twist lock pins 144, as
explained below, for
releasably securing devices 46 to upper swivelling mechanism 61 which as
stated earlier is part of
an elevating assembly 60 as described later.
[00140] Along a portion of pathway 15, a series of rockets 18 and variants
thereof, and
other items such as lateral conveying devices 46, carriages 20 and variants
such as pressurized
tourist carriages and launching system servicing carriages, are stored on
storage racks 7 which are
divided by walls 64. Rockets 18, if they do not use solid fuel, can be fuelled
during storage on
racks 7 or preferably in assembly bays 10 using various combinations of
propellant such as liquid-
liquid or liquid-solid fuels depending on the type of rockets 18. One high
specific impulse
propellant combination is liquid oxygen (LOX) and liquid hydrogen (LH2) which
can be stored in
storage tanks 65 and 66 respectively, as shown in Fig. 5.
[00141] This fuel combination can be produced in a most environmentally
friendly manner,
by using a system wherein one or more hydro-turbines deliver mechanical power
and possibly
other hydro-turbines drive electrical generators 62 which are included in a
power facility 468.
The hydro-turbine(s) receive water from an appropriate source, such as a river
with sufficient
pressure and mass flow rate, to power an electrical substation 70 from coupled
electrical
generators 62, and directly drive compressors as found in gas liquefaction
plants such as a water
electrolysis and gas liquefaction sub-plant in plant 74. Electrical power from
substation 70 can be
used to operate water electrolysis sub-plant in plant 74, and may be used to
provide auxiliary
power to a hydro-turbine driven gas liquefaction sub-plant in plant 74 for
liquefying the resultant
oxygen (02) and hydrogen (H2), which are respectively stored in LOX storage
tank 65 and LH2
storage tank 66, as well, the electrical power being used to supply energy to
all other parts of
launch system 1 and its supporting apparatus requiring such power. Other
sources of energy such
as nuclear fission may be used as an alternative if hydroelectric and hydro-
turbine derived shaft
horse power are not available. Renewable sources of energy such as geothermal,
hydropower or
solar are preferred.
[00142] As explained earlier, rockets 18 are transported on the ground
while being
contained in carriages 20. Lateral conveying devices 46 can move along paths
14 and 14A, and
pathway 15 on relatively narrow, parallel rails 17 (compared to tracks 90
discussed hereinafter).
An empty carriage 20 on storage rack 7 is shown in Figs. 5 and 6 next to an
empty lateral
conveying device 46. Also shown in Fig. 5 is a pressurized tourist carriage
variant, service
carriage vehicle variant, spare balloon containing carriages or a space
tourism aerospace plane 76.
Tracks 78 and a pair of tracks 90 (discussed below) (Figs. 5 and 6), running
parallel to the straight
opposing parts of path 15, are used for the movement of crane 48 and wheeled
transfer loader 50.
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Empty carriages 20 are shown on top of lateral conveying devices 46 moving
along pathway 15,
from which they can be removed for refurbishing or reloading.
[00143] The loading system is shown in further detail in Fig. 6.
Storage racks 7 each hold
either complete rockets 18 and/or component parts of rocket 18, shown as
rocket parts 18A, 18B,
and 18C, and/or a space tourism aerospace plane 76 (Fig. 5), and/or empty
carriages 20 or spare
lateral conveying devices 46. Rocket parts 18A-18C could be combined for a
final rocket 18, but
the invention is not so restricted. Rockets 18 with the respective rocket
parts 18A-18C are fed to
their respective places by means of railway 3 (see Fig. 1), which rockets 18,
rocket parts, etc.
= could come from distant manufacturing facilities worldwide. Carriage 20
and a lateral carrying
device 46 are also shown in racks 7. Crane 48 can travel on tracks 78 to
assemble rocket parts
18A-18C in a bay within the storage racks 7 and then into one of carriages 20.
Crane 48 may also
be used to service paths 14 and 14A, and pathway 15. Crane 48 has a cable 49.
Crane 48, using
its cable 49 with appropriate lifting gear, may lift assembled rocket 18 and
carry it into bay 10
(left part of Fig. 6) for insertion into a preplaced carriage 20 atop lateral
conveying device 46. A
crane 48 is needed in addition to the other service equipment noted above, for
servicing the tracks
17, 78 and 90 and rails 97 (discussed hereinafter). Care must be taken in
using crane 48 for
transferring rockets 18, since crane's cable 49 may tend to sway during
transfer and the rocket
suspended from cable 49 could be damaged.
[00144] As explained below, there is always a risk of accidental
detonation of a rocket 18
in bay 10 if highly reactive fuel-oxidizer combinations are used. In order to
protect the various
structures, equipment and personnel from the blast effects of such a
detonation, a pair of parallel,
inverted L-shaped guide members 80 (Fig. 6) extend over opposite edges of bay
10. Each pair of
guide members 80 has a blast cover 82 slidable in the direction shown by
arrows E, and blast
cover 82 is slid under overlapping flanges 84 of guide members 80 prior to
fueling. Blast cover
82, once located under flanges 84, cannot be moved even if a blast occurs.
Blast covers 82 are
made of such a material as not to be destroyed even if it has to withstand a
blast within bay 10
during assembly, fuelling or otherwise, the blast being directed away from
critical components via
chute 86.
[00145] Transverse loader 50, shown in Figs. 1 and 6, is part of a
rocket loading system 88
including the pair of wide tracks 90 (wider than tracks 78 for crane 48) upon
which ride the pair
of wheeled trucks 92. A guide assembly 94 comprising beams 96 and wheeled
trucks 92 extends
across wide tracks 90 and ride on trucks 92 which move on wide tracks 90.
Guide assembly 94
has parallel rails 97 as shown in Fig. 7 on top of beams 96 across which
travels elevator assembly
100. The entire transverse loader assembly 50 atop rails 90 is similar to a
top running double
girder crane with end trucks. Parallel guide beams 96 are affixed to trucks
92. Wheeled truck 98
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moves across parallel rails 97 as shown in Figs. 1, 1A, 6 and 7. Transfer
loader 50 includes
elevator assembly 100 as shown in Fig. 7 with a guide support apparatus 101
and an elevator 102
movable upwardly and downwardly as shown by the arrow F in support apparatus
101 using
appropriate electro-mechanical means, preferably counterweighted. Transfer
loader 50 removes
rockets 18, or empty carriages 20 or variants thereof, or carriages 20 holding
various types of
rockets 18 or various components, from storage racks 7, to assembly bays 10,
from which lateral
carrying devices 46 transport the fueled rockets 18 within carriages 20 or
other carriage variants
to launcher 119.
[00146] Referring further to Fig. 7, one embodiment of the details of the
upper portion of
transverse loader 50 in slightly modified form is shown. As noted above,
transverse loader 50 has
elevator assembly 100, with guide support apparatus 101 in which is deposed
elevator 102.
Support apparatus 101 is shown having opposing extensions 103 which permits
the connection of
apparatus 101 to wheeled truck 98 for moving elevator assembly 100 across
rails 97 on top of
beams 96. In order to engage a rocket 18 for lifting, elevator assembly 100
has depending legs
105 of which a minimum of three is preferred for stability, which are
connected to a body 106
affixed to the lower end of elevator 102 permitting a grasping assembly 104 to
be lowered into
assembly bay 10, as indicated by arrow G. Legs 105 are movable radially in
guides 110 (as shown
by arrows H in Fig. 7A) with respect to a rocket 18 located between legs 105
so as to
accommodate different diameter rockets. A fractional rotation twist lock pin
111 or other means
of attachment to rocket 18, is located at the free end of each leg 105, and
the upper portion of
rocket 18 has equally spaced fractional rotation twist lock pin sockets 109 or
other receptacles for
other means of attachment, for receiving the respective twist lock pins 111
for enabling the secure
attachment of rocket 18 to elevator assembly 100. Pin sockets 109 are disposed
in a nose portion
19 of rocket 18, are generally parallel to the longitudinal axis of rocket 18.
Pin sockets 109 may
have access covers 113 attached to nose 19 of rocket 18, but being removable
from the respective
sockets 109 as required to provide access to socket 109, while providing a
smooth surface to
rocket 18 when pin sockets 109 are not in use to reduce aerodynamic drag when
the rocket is in
flight.
[00147] Upper and lower stabilizing arm assemblies 114 may be provided for
stabilizing a
rocket 18 during lateral travel, held on elevator assembly 100 while
travelling along tracks 90 and
rails 97. Stabilizing arm assemblies 114 each have a hydraulic or other
actuator 115 to which is
attached an arm 116 of each arm assembly 114. Arms 116 are rotatable along
paths indicated by
arrows I. A lug 117 is provided at the free end of each arm 116 for engaging
an appropriately
configured recess 118 in rocket 18 for receiving each of lugs 117.
[00148] As discussed previously, Fig. 6 shows a lateral carrying device 46
loaded with a
CA 02875464 2014-12-18
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carriage 20 holding a rocket 18 moving in pathway 15 towards launcher 119
discussed below. Another
lateral carrying device 46 carrying an empty carriage 20 is traveling away
from launcher 119 which
dispensed a rocket 18 from carriage 20 at high altitude, moving in pathway 15
returning to an unoccupied
assembly bay 10 to be reloaded with rocket 18 or returning to storage rack 7
for servicing if required.
[00149] Referring back to Fig. 5, rocket launch system 1 further includes
launcher 119. A local
launch control bunker 120 directs the operation of rocket launch system 1,
directing the flows of electrical
energy to and from adjacent launch systems 1 from energy sources such as power
facility 468 or other
adjacent rocket launch systems 1, and housing the computer control and
surveillance systems, utilizing data
from the various measuring and imaging devices placed throughout launch system
1. This is where the
personnel are generally located for controlling the local rocket launch system
1 and coordinating launches
from the other members of the group of launch systems for minimizing the use
of energy.
[00150] Elevating assembly 60 is disposed beneath the ground as shown in
Figs. 2, 8 and 9.
Elevating assembly 60 may have an elevating mechanism such as a hydraulic
piston rod 68 upon which sits
upper swivelling assembly 61 (Fig. 9) for rotating, by means of a rotary drive
134, a carriage 20 with rocket
18 within, loaded on lateral conveying device 46 in the direction shown by
arrow J. Elevating system 60
described in more detail below with respect to Fig. 8, includes rod 68 having
a wide, non-rotating lower bed
135 fixed to rod 68, mounted for supporting upper swivelling assembly 61.
Upper swivelling assembly 61 is
composed of a rotatable bed 136 (with a table portion 141) mounted on top of
non-rotating lower bed 135
(which is not part of turntable mechanism 63).
[00151] Reference is now made to Figs. 8 and 9. Piston rod 68 is part of
a piston 67 extending from
a hydraulic cylinder 69. Hydraulic cylinder 69, piston 67 and rod 68 do not
rotate.
[00152] The foregoing hydraulic system is not the only way to operate the
elevating mechanism.
An electro-mechanical system could form the elevating mechanism.
[00153] Turning next to Fig. 10, turntable mechanism 63 is an above
ground portion of rocket
launcher 119 for receiving rocket-loaded carriages 20 from elevating assembly
60 and orienting them to be
transported is shown. The upward movement of rocket-loaded carriage 20 is
shown by the arrow L. As stated
above, turntable mechanism 63 includes turntable base 122 and turret assembly
123. Turntable base 122 is
attached to the earth.
[00154] Turntable 72 could be quite heavy, weighing several tons, and
should be supported by a
structure able to support such a heavy load, to withstand uplift and lateral
forces, and rotate smoothly.-A
detail of an appropriate turntable support device is shown in Fig. 8A.
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[00155] Fig. 8A shows turntable base 122 having a horizontal surface of a
wheel engaging base 270
for being engaged by wheels 284, an upstanding tubular part 272, and a
horizontal, annular flange 274
=extending outwardly towards the outer circumference of turntable base 122.
Turntable 72 has a downwardly
extending tubular part 276 at the perimeter of turntable 72, from which
extends an inwardly extending
horizontal, annular flange 278 having a number of wheel axle holders 280, 281
and 282 extending towards
wheel engaging base 270, upstanding tubular part 272 and horizontal, annular
flange 274, respectively. Each
axle holder 280, 281 and 282 respectively holds the axles of wheels 284, 286
and 288 respectively. Wheels
284, 286 and 288 ride on the surfaces of wheel engaging base 270, upstanding
tubular part 272 and
horizontal, annular flange 274 to enable the smooth circular rotation of
turntable 72 shown in FIG. 8 by the
arrow K. Alternatively, referring to FIG. 8B, turntable base 122 could have a
horizontal bearing base 290, an
upstanding tubular part 291 and a horizontal, annular flange 292. Likewise,
turntable 72 could alternatively
have a downwardly extending tubular part 293 and an inwardly extending
horizontal, annular flange 294. A
set of bearing balls or crossed rollers 295 is located between horizontal,
annular flange 294 and each of
bearing base 290 and horizontal, annular flange 292, and appropriate annular
bearing grooves 296 would be
used to enable the rotation of turntable 72 with reduced friction than if
bearings were not provided.
[00156] Turntable 72, based on the size =of carriage 20, could be about
46 feet in diameter. For
example, if the tubular interior of carriage 20 for containing rocket 18 has a
radius of 8 feet, and the
minimum thickness of carriage 20 holding rocket is 2 feet, with a clearance of
centrally located carriage 20 is
3 feet, the diameter of turntable 72 would be about 46 feet. This is shown in
Fig. 8C.
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If R = 8'
A = 2'
a = R+ A = 8' + 2' = 10'
in A AOB
OB = 2a = 20'
AB = a(43) = 1043 = 17.32'
carriage side 2AB = 34.64'
OC = OB + BC = 20' + 3' = 23'
.. Diameter of turntable is at least 2 (OC) = 46'
[00157] For a modest diameter of the tubular interior of carriage 20 for
containing rocket
18 of 16 feet, carriage interior diameter, plus a modest (A = 2 feet)
clearance for the structure of
carriage 20, and allowance of 3 feet (8 = 3 feet) for the mechanism to permit
turntable 72 to
rotate, the diameter of turntable 72 is about 46 feet and a flat side 22 of
carriage 20 is about 34.6
feet.
[00158] Turret assembly 123 is located at ground level, above bed 136 (Fig.
8), and is
supported and restrained by turntable base 122. The vertical axis of rotation
of turret assembly
123 coincides with the axis of elevating assembly 60. Lower guide tube 124 has
an orifice 71 for
receiving rocket-loaded carriage 20 from lateral carrying device 46 through an
orifice 73 as
shown in Fig. 10 extending through turntable 72 and turntable base 122, by
means of elevating
assembly 60. Rotatable bed 136 (Figs. 8, 9) has tapered alignment pins 142 and
fractional twist
lock pins 144 to releasably lock lateral conveying device 46 with carriage 20
thereon to bed 136.
Carriage 20 is releasably locked in a similar manner to lateral conveying
device 46 using
alignment pins 142 and fractional twist locking pins 144. Being so releasably
locked, carriage 20
may be driven as explained further below.
[00159] Still referring to Figs. 8 and 10, turret assembly 123 further
includes turntable 72
rotatable with respect to turntable base 122 in the direction shown by arrow K
noted earlier, a
yoke 126 having a pair of parallel, spaced apart, arms 127 which are pivotable
above turntable 72.
Between said arms 127 is disposed lower guide tube 124 (also part of turret
assembly 123). A pair
of horizontal coaxial pivot pins 128 extends through each of arms 127 and into
opposing walls of
lower guide tube 124, and is disposed through a pair of support members 129.
Internal carriage
guides 133 extend along the internal cylindrical walls of lower guide tube 124
and are separated
from each other by 120 for entering a set of corner recesses 130 (Fig. 9)
extending in a
longitudinal direction along the corner edges of carriages 20. The corner
recesses contain traction
drives 26. Lower guide tube 124 and secondary guide structure 125 pivot in the
rotational path
shown by the arrow M in Fig. 8 by means of an appropriate rotational drive
system, about the
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same horizontal axis defined by pins 128. Each of arms 127 includes a
counterweight 131
discussed below. The center point of lower guide tube 124 is disposed
vertically above 'turntable
72 of turret assembly 123 so that the axes of rotation of each of turntable
and lower guide tube
124 intersect orthogonally. The vertical axis of rotation of turntable 72
being coincident with the
axis of elevating assembly 60 and any lateral conveying device 46 and carriage
20 situated
thereon.
[00160] Secondary guide structure 125 has an integral tube 143 which is
held at a fixed
distance from the common pivot of itself and lower guide tube 124. Thus,
secondary guide
structure 125 is counterbalanced about its horizontal pivot and has internal
carriage guides 138
within the integral tube. The lower end of integral tube 143 of secondary
guide structure 125 is
capable of coming in alignment with the upper end of lower guide tube 124 so
the tubes are
coaxial, and internal carriage guides 133 and 138 are also aligned. Lower
guide tube 124 is
rotatable about coaxial pivot pins 128, and rotates until its outer surfaces
engage a stop 132 (Fig.
10) extending from an integral tube 330 so that carriage guides 133 and 138
are in alignment.
Carriage guides 133 and 138 are powered in the same manner as are power cables
27 (as
discussed below) so that traction drives 26 in carriage 20 can utilize the
power. The upper end of
the tube of secondary guide structure 125 has internal transitional attachment
points for primary
cables 27 to permit carriage 20 to move from internal carriage guides 138 onto
primary cables 27.
[001611 As shown in Fig. 2, lateral conveying devices 46, each loaded with
a carriage 20
holding a rocket 18 moves along pathway 15 from assembly bays 10. Carriage 20
with rocket 18
is removed from pathway 15, transferred to rocket launcher 119, and after the
rocket is launched
the empty carriage 20 is returned to the empty lateral carrying device 46
before proceeding along
pathway 15, returning to assembly bays 10 or storage racks 7.
[00162] Turning to Figs. 8-10, elevating assembly 60 raises or lowers
carriage 20 with
lateral conveying device 46 secured to rotatable bed 136, by raising piston 67
and rod 68 in the
direction shown by arrow N (showing the raising and lowering directions) to
move carriage 20
into lower guide tube 124, and clear of turntable 72. Rotatable bed 136 has
structure described
below for releasable attachment to lateral conveying device 46 to accurately
align traction drives
26 of carriage 20 with appropriate internal carriage guides 133 of lower guide
tube 124.
[00163] Elevating assembly 60, lateral carrying device 46 and carriage 20
are shown in
more detail in Figs. 8 and 9. Hydraulic piston 67 has on its upper end upper
swivelling assembly
61 composed of non-rotating lower bed 135, rotatable upper bed 136 and table
portion 141.
Lateral conveying devices 46 can travel to a location centered over elevating
assembly 60. As
mentioned earlier, tracks 17 are likely to be of necessity wider than
conventional railroad tracks.
Upwardly tapered alignment pins 142 (four are shown) (shown in detail in Fig.
9A) extend from
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table portion 141 as do fractional twist lock pins 144 (four are shown) (shown
in detail in Fig.
9B). These interconnect with lateral conveying device 46 as explained below.
Of course, the
location of the respective pins 142 and 144, and the respective sockets could
be reversed between
the lateral conveying devices 46 and the portion 141.
[00164] Upper swivelling assembly 61 of elevating assembly 60 is mounted
on rod 68 and
can be raised as shown by arrow N to permit engagement of lower tapered
alignment pins 142 and
fractional rotation twist lock pins 144 shown in Fig. 9 into corresponding
alignment pin sockets
152 and twist pin socket 154 in lateral conveying device 46.
[00165] = The upper surface of lateral conveying device 46 has upwardly
extending tapered
alignment pins and fractional rotation pins which are virtually the same as
lower tapered
alignment pins 142 and fractional rotation twist lock pins l 44 extending from
the top of table
portion 141. A corresponding alignment pin socket 155 and a twist lock socket
153 are provided
in the lower face of carriage 20 to receive the tapered alignment pins and
fractional rotation pins
on the top of device 46 to releasably attach carriage 20 to lateral conveying
device 46.
[00166] Lateral conveying device 46 has four wheels 58 positioned and
contoured to ride
on electric rails or tracks 17, and including tracks 17 adjacent to table
portion 141, and are
independently alignable as mentioned earlier. Lateral conveying device 46 may
be powered from
electric rails 17 in ways similar to electric trains or tram cars (which would
have to be connected
to an electric power source) or from some other on board power source such as
fuel cells or
internal combustion engines.
100167] Lower guide tube 124 has internal carriage guides 133 (Figs. 8,
10) which extend
into each of corner recesses 130 extending along the vertical intersections of
sides 22, also shown
in enlarged form, (Fig. 10) of carriage 20 to engage traction drives 26 of
each carriage 20 to move
each carriage 20 along carriage guides 133, and to maintain the orientation of
carriage 20 in lower
guide tube 124. Carriage traction drives 26 are provided for gripping primary
power cables 27.
Carriage traction drives 26 are mechanisms having cross sections partially
enveloping primary
cables 27 on which carriages 20 ride, and from which they derive power or to
which they deliver
power. Referring to Fig. 15C, one of traction drives 26 is shown as having two
opposing traction
drive wheels 26A in engagement with primary cable 27. Each traction drive 26
includes a
gearbox G and motor-generator M-G. As mentioned earlier, traction drives 26
may include
motor-generators M-G and gearboxes G and opposing cylindrical wheels 26A
operatively
connected thereto, each having an annular groove 137 for receiving a cable 27
as shown in Figs.
9C, I5C and 25. Wheels 26A rotate in opposite directions as shown by arrows 01
and 02.
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Traction drives 26 are positioned along the length of a carriage 20. Surface
roughening or
modification could be provided on the gripping surfaces of traction wheels 26A
to enhance the
appropriate surface friction of the pairs of traction drive wheels 26A which
in effect pinch
respective cables 27. Electric motor-generators M-G of tiaction drives 26
derive electrical power
from primary cables 27 (and any subsequent cables), to drive/rotate respective
pairs of wheels
26A through gearboxes G as carriages 20 ascend primary cables 27, and motor-
generators M-G
provide electrical power to primary cables 27 as carriages 20 descend primary
cables 27. The
motors could rotate more than one pair of
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traction drive wheels 26A. There also could be individual motors operatively
connected to
individual pairs of traction drive wheels 26A. Much of this depends on the
load being carried and
the size of carriage 20.
[00168] Traction drives 26 propel carriage 20 along cables 27 or guides 133
and 138 (Fig.
10). Traction drives 26 generate power which is returned to the cables when
each carriage 20 is
propelled in a reverse direction by gravitational force. The generation of
this power causes a
reaction to the gravitational force and retards the motion of empty carriage
20 as it moves in a
downward direction as occurs some time after launch of rocket 18. Each
traction drive 26 can
have a minimum of one opposing pair of wheels 26A, as shown in Fig. 25. The
traction drive
motors should be of a constant torque motor or of a variable frequency drive
type to compensate
for cable stretch or wheel slip, to cause each group of wheels to contribute
equally and maintain
the carriage co-axial with the centroid of cables 27 or internal carriage
guides 133 of lower guide
tube 124 or internal carriage guides 138 of integral tube 330 of secondary
guide structure 125
when driving carriage 20 upwards.
[00169] As noted earlier, rocket launcher 119 according to the present
invention has an
elevating assembly 60 for raising or lowering a carriage 20 vertically into or
out of engagement
with lower guide tube 124 mounted on turntable 72 of turntable mechanism 63.=
Lateral conveying
device 46 is movable with respect to table portion 141 so that fractional
rotational twist lock pins
144 can be received in twist pin sockets 154 in the bottom of lateral
conveying device 46.
Elevating assembly 60 elevates table 141 a short distance out of the bed of
tracks 17 to engage the
bottom of lateral conveying device 46. Table 141 is then locked onto the
bottom of lateral
conveying device 46 before its wheels 58 and all of the table portion 141 are
lifted above tracks
17 whereupon table portion 141 may be rotated with lateral carrying device 46
and carriage 20
mounted thereon by means of rotating drive 134 to align carriage traction
drives 26 with intemal
carriage guides 133 in lower guide tube 124 which rotates freely or, if
necessary with power
assist, with turret assembly 123 to maintain alignment with the changing
winds. This assures the
necessary stable alignment of carriage 20 with rocket 18 held therein, in
lower guide tube 124.
[00170] Referring to Figs. 1, 10 and 11, rocket launch system 1 includes a
primary set of
cables 27 which are separated from each other by spacer or stabilizer
assemblies 158. Spacer
assemblies 158 are shown in detail in Fig. 10A, and include three side pieces
159 forming a
triangle, and arms or flanges 161 orthogonal to the plane-of said triangle for
engaging respective
cables 27. Flanges 161 or side pieces 159 or both, are made of electrically
non-conductive
material. Cables 27 are capable of conveying electrical power, are of
lightweight as explained
below, and have a high tensile strength. The preferred construction and manner
of employment of
spacer assemblies 158 is shown in Fig. 10A. Extending from each of cables 27
are adaptive
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- 27 -
connectors 501 (each similar to an adaptive connector 247 discussed below).
Adaptive
connectors 501 are provided along each primary cable 27 at spaced intervals,
connectors 501
being in alignment along respective cables 27. Each adaptive connector 501 has
a pair of spaced,
parallel aligned flanges 503 generally radially (but not exactly radially
since they clamp loops of
wire extending from the respective cables 27) adjacent respective cables 27.
Flanges 503 each
have a pair of columns 505, 506 of holes, each column of holes 505, 506 on
each pair of flanges
503 being in alignment. The column of holes 506 being closest to respective
cables 27 are
attached to cables 27 as explained later with respect to an adaptive connector
247. A set of lugs
(not shown) extend through the respective aligned holes 505 and also holes in
alignment on
respective orthogonal flanges 161 to attach each corner of respective spacer
assemblies 158 to
respective primary cables 27. Each arm 159 of the respective spacer assemblies
158 has an
enlarged portion 520, preferably of tubular construction for stiffness and
resistance to buckling,
extending between adjacent primary cables 27, which have shoulders or tapering
surfaces 522 to
help restrain movement of cables 27 with respect to each other, and to create
a lateral clearance
between spacer assembly 158 and each cable 27. Arms 159 have smaller end
portions 524 for
attachment to each other and to respective orthogonal arms 161. Spacer
assemblies 158 can have
various configurations; spacer assemblies 158 are shown having square cross
sections, but circular
cross sections are also advantageous. Spacer assemblies 158 can each be one
piece, being bent
into their triangular shapes and slipped onto three primary cables 27, or arms
159 can be welded
together before or after installation on cables 27. Arms 159 are preferably
welded to spacer
assemblies 158 although bolted connections are possible.
[001711 At the
uppermost part of the rocket launch system 1 is the set of lighter-than-air,
tensioning balloons 160 (Figs. 1, 1B, 12-14), and there are other lighter-than-
air tensioning
balloons 164 (Figs. 1, 1B, 11, 15, 17, 18, 21) positioned along the cables 27
for offsetting the self
weight of cables 27 and somewhat contributing to their tensioning. Balloons
160 are connected to
a tensioning balloon attachment frame or top large harness 162 (shown in Figs.
12-14) for the
purpose of supporting the part of the weight of the primary cables 27 and all
components above
other tensioning balloons 164, docking station 166 (Fig. 13 discussed below),
inclusive of the
operational weight of a carriage 20 with a flight ready rocket 18. Balloons
160 and 164 must
accommodate any lift fluctuations and reaction forces due to the movement of
carriage 20 and its
contents, and other components. There are variations in lift from tensioning
balloons 160 and 164
due to daily thermal and atmospheric pressure variations. An additional amount
of lift is required
to cause primary cables 27 to be tensioned to a significant part of their safe
working load, since
cables 27 must be kept as close to vertical as practical. As noted, one or
more additional sets of
lighter-than-air balloons 164 or 164A (Figs. 1, 11, 15, 16, 17, 20A, 20B),
which can be smaller
CA 02875464 2014-12-18
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than lighter-than-air balloons 160, must be interspersed along cables 27 to
relieve the self weight of cables 27
and the weight of the supporting structure and spacer assemblies 158 of
primary cables 27 together with daily
thermal lift variations with a margin of safety to prevent cable breakage
under self weight, the net effect
being that cables 27 with associated balloons approximate cables with no
weight or negative weight. Primary
cables 27 are engaged by and provide power to a winch or hoist 169 discussed
below, and form a cableway
path 170 shown in Figs. 11 and 13. Cableway path 170 is formed of and enclosed
by primary cables 27,
which carriage 20 engages and from which derives power so it can travel along
cables 27. Tensioning
balloon attachment frame 162 is composed of an upper ring 145 and a lower ring
146 (Figs. 13-14) which are
counter rotational, about a rotary bearing 149. Upper ring 145 and lower ring
146 are driven by a geared
rotational drive system 177, and are described below.
[00172] Docking station 166 is shown in Figs. 13 and 14. Docking station
166 has upper ring part
172 which can be rotated with respect to a lower ring part 174, parts 172 and
174 being engagable with a ring
bearing 176, are driven by a geared rotational drive system 147 (also see Fig.
28 for a corresponding
rotational drive system 379), which includes and is assisted by reaction force
thrusters 178. Geared rotational
drive systems 177 and 147 are also used to provide the opposed rotation of
upper ring 145 with respect to
lower ring 146 of tensioning balloon attachment frame 162, and also of upper
ring part 172 and lower ring
part 174 of docking station 166 mentioned above. The rotational drive systems
177 and 147 of tensioning
balloon attachment frame 162 and docking station 166, respectively, are
coordinated so that all components
between and inclusive of, upper ring part 172 and lower ring 146 rotate
together as a unit, with associated
cables kept from twisting around each other. Force thrusters 178 and 148
counter wind induced rotation or
rotation resulting from the rotation of a carriage 20, when the lower end of
carriage 20 is held within upper
ring part 172 of docking station 166, and carriage 20 is being rotated into an
optimal direction for launch.
Docking station 166 has two sets of three internal carriage guides 180A, 180B
(Figs. 13, 14) for entering
radial recesses 130 of each carriage 20 to keep the respective carriages 20 in
proper alignment and stable,
while supplying electrical power to the carriage traction drives 26.
[00173] Still referring to Figs. 13 and 14, lift ring assembly 182 is
shown. Lift ring assembly 182
includes a short tubular ring 183 with a triangular or possibly circular cross
section, and is guided by and is
electrically connected to secondary cables 184 extending upwards from upper
ring part 172 of docking
station 166 to connect to lower ring 146 of tensioning balloon attachment
frame 162. Tertiary cables 186
(Figs. 13, 14) extending upwardly from lift ring assembly 182 to the frame of
a lower hoist assembly 198.
Lift ring assembly 182 is guided by and derives electrical power from
secondary cables 184 which are
connected to docking station 166. Lift ring assembly 182 is supported by
tertiary cables 186 which are
connected to a lower hoist carrier 200 which is the frame of lower hoist
assembly 198. Referring to
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Fig. 14A, carriage end gripper 196 is provided with a set of four orifices 195
through which secondary cables
184 freely pass, and a pair of orifices 197 through which tertiary cables 186
freely pass. Electrical power for
carriage end gripper 196 can be provided by secondary cables 184.
[00174] Tubular lift ring 183 has a set of inwardly extending guide
structure elements or internal
carriage guides 188 which are engaged in the respective three recesses 130
extending longitudinally in
carriage 20 for maintaining the orientation of carriage 20 in tubular lift
ring 183 and supplying power to
carriage 20. Lift ring assembly 182 comprises tubular lift ring 183, a
carriage pivoting assembly 189 which
itself includes a pair of opposing pivot pins 190 and a rotational drive
system 194, lift ring guides 192 and
reversible traction drives 193. Rotation drive system 194 rotates tubular lift
ring 183 which is pivotable about
the horizontal axis defined by pins 190. The center of gravity of tubular lift
ring 183 is made to fall in its
geometric center which is co-incident with the axis of pins 190. Tubular lift
ring 183 has a clamping or
locking mechanism to permit it to be releasably attached to carriage 20 in
such a manner that center of
gravity 36 of carriage 20 is held on the axis of pins 190. The axis of
rotation of reversible variable pitch
thruster 31 is made parallel to the horizontal axis defined by pins 190.
TertiarST cables 186 are respectively
connected to the respective lift ring guides 192. Tertiary cables 186 are
provided in two groups of cables of
fixed length, and are attached to lower hoist carrier 200 180 apart, to
connect carrier 200 to lift ring guides
192 below and assist in guiding the movement of carriage end gripper 196
(discussed below), and carries
electrical power if needed.
[00175] Lift ring assembly 182 includes rotational drive system 194 to
change the elevation angle
indicated by the arrow P (Fig. 13) of tubular lift ring 183 and carriage 20
held thereby with respect to cables
184 and 186. Carriage end gripper 196 is also shown in Figs. 12, 13 and 14.
Carriage end gripper 196 can be
supported by a lower hoist cable 201 attached to lower hoist assembly 198
mounted on lower hoist carrier
200. Lower hoist cable 201 moves in the directions indicated by the arrow Q in
Fig. 14. Carriage end gripper
196 is guided in motion by secondary cables 184 which carry electrical power,
and supported by tertiary
cables 186. Carriage end gripper 196 is able to releasably lock to the top of
a carriage 20 by means of locking
pins 204 which cooperate with pin lock receptacles 32 in the upper part of
carriage 20. When carriage end
gripper 196 is firmly connected to carriage 20, carriage end gripper 196 is
able to lift or assist in lifting
carriage 20 from docking station 166 and up through lift ring assembly 182
until center of gravity 36 of
carriage 20 coincides with the horizontal pivot axis of lift ring assembly 182
defined by pins 190 when lift
ring assembly 182 is lowered into contact with upper ring part 172 of docking
station 166. The length of
cables 186, which guides the motion of end gripper 196 must be long enough to
permit carriage 20 to rotate
about the horizontal axis when end gripper 196 detaches from carriage 20 and
is lifted a short distance out of
engagement with docking assembly 166.
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[00176] Lower hoist assembly 198 is fixed to the lower end of lower hoist
carrier 200 as noted
above, and also as noted above is used for lifting or assisting the traction
drives 26 of carriage 20 in moving
carriage 20 into and out of engagement with tubular lift ring 183. Lower hoist
carrier 200 is raised and
lowered as indicated by arrow R on hoist cables 202 from upper hoist 168
attached to tensioning balloon
attachment frame 162 shown in Figs. 12, 13, and 14. Power is provided to hoist
169 through secondary
cables 184. Either three-phase current or direct current can be used to power
hoist 169. In the three-phase
current system as shown, the group of four secondary cables 184, further
identified (Fig. 14) from left to
right as cable 184A is phase one of three, cable 184B is phase two of three,
cable 184C is phase three of
three and 184D which may be used as an electrical neutral or as a duplicate of
phase one of three. Also as
noted earlier, lighter-than-air balloons 160 support the upper components of
rocket launching system 1 and
provide a significant portion of the tension required to keep primary cables
27 and secondary cables 184 in
tension so as to make them taut, even with operational loads. As shown in
Figs. 12, 13 and 14, tensioning
balloon attachment frame 162 is disposed beneath lighter-than-air or
tensioning balloons 160.
[00177] Referring to Figs. 1, 1B, 11, 15, 16, 17, 20A and 20B, these
figures show a number of
groups of smaller lighter-than-air ballo?ns 164 or 164A used to relieve the
self weight of cables 27 and
associated support structures and spacer assemblies are shown. Balloons 164
are tapered and balloons 164A
are cylindrical, although other shapes and configurations are possible and
fall within the scope of the
invention. Each of a number of large harnesses 206 having tensioning balloon
holders 208 is attached to
primary cables 27 by means of a three-sided lower spacer or stabilizer
assembly 210. Each lower spacer
assembly 210 is constructed and attached to primary cables 27 in the same
manner as spacers 158 were
constructed and employed as described earlier. Balloons 164 or 164A are
respectively connected to balloon
holders or attachment points 208 (Fig. 18). Lower spacer assembly 210 has
three arms 211 forming an
equilateral triangle as viewed in plan, arms 211 being parallel to respective
arms 222 of large harness 206.
Lower spacer assembly 210 has a connecting structure 214 at the respective
intersections of arms 211, from
which leads 215 extend. Each lead 215 from lower spacer assembly 210 extends
for attachment to the
respective balloon holders 208 of large harness 206. There are also provided a
number of upper spacer or
stabilizer assemblies 216 which, like spacer assemblies 210, separate primary
cables 27 and further hold in
place cable ties 218 and 219. Upper spacer assemblies are constructed and
employed as are spacer assemblies
158 and lower spacer assemblies 210. Each upper stabilizer 216 has three arms
217 forming together in a
plan view, an equilateral triangle, arms 217 being parallel to respective arms
222. A cable connector 220 is at
the intersection of the respective arms 217. Pairs of stabilizing ties 218 are
connected at one end to a cable
connector 220 at opposite ends of arms 217 and to tie holders 221 at the
midpoint of arms 222 parallel to
respective arms 217. Another set of cable leads 219 is connected between tie
connectors 220 and balloon
holders 208. This arrangement assists in holding harness 206 stably in place.
Harnesses 206 are installed
periodically with balloons 164 and 164A, respectively, along the length of
primary cables 27 to compensate
CA 02875464 2014-12-18
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for the self weight of cables 27 and any attached structures, and to induce
tension in the cables to assist in
keeping them upright.
[00178] A specific assembly for connecting the various components of upper
spacer 216 is as follows.
Upper spacer assembly 216 and the items connected to them are shown in Figs.
15A, 15B and 15C. As noted
above, upper spacer 216 is composed of three arms 217 forming an equilateral
triangle. Referring to Figs.
15B and 15C, cable connector 220 comprises a base plate 902 having a central
arm 904 and two arms 906
and 908 separated from central arm 904 by an angle exceeding 900. Cable
connector 220 further has a
support portion 910 which is generally opposite arm 904. Base plate 902 is
advantageously flat, and
extending perpendicularly thereto is a cable connecting flange 912 which
extends along the middle of
support portion 910. A pair of arm support flanges 914 and 916 also extends
perpendicularly from base plate
902 and are equiangularly spaced from cable connecting flange 912. Arms 904,
906 and 908 have lug-
receiving holes 920, 918 and 922 respectively, extending perpendicularly
through the respective arms 904,
906 and 908. Cable connecting flange 912 has a series of equally spaced, lug-
receiving holes 924 extending
along the height of flange 912.
[00179] Each cable 27 has at least one, and more likely, many, connecting
structures 925, each
connecting structure 925 being composed of pairs of parallel, opposing, spaced
flange-receiving connecting
flanges 926, 927 which are parallel to the respective axes of cables 27.
Flange 926 has parallel aligned
columns of lug-receiving holes 928 and 930, which are aligned with
corresponding holes 928, 930 on the
other flange 927. In order to attach each cable connector 220 to a position on
a respective cable 27, cable
connecting flange 912 is inserted between flange-receiving connecting flanges
926, 927 with holes 924 in
alignment with each of the respective holes 928. A set of lugs 932 is inserted
into the respective aligned
holes 928 and 924 and attached to a nut or other fastener receiver 933. To
further connect respective cable
connectors 220 to respective cables 27, similar bolts 256 as shown in Fig. 22
are used to clamp loops 244 of
cable 27. Flange-receiving connecting flanges 926, 927 are close enough to
each other to enable traction
drives 26 to engage respective cables 27 as carriages 20 with traction drives
26 pass flanges 926 and 927 in
full operative engagement with respective cables 27.
[00180] As noted earlier, pairs of stabilizing ties 218 connect cable
connector 220 to
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respective midpoints of a pair of arms 222 of large harness 206. Each
stabilizing tie 218 has at
one end a connecting yoke 934 with a pair of parallel flanges 936 with aligned
holes 938 through
which extends a lug 940 which also passes through hole 908 for subsequent
reception by a nut or
other fastener receiver 942 to connect stabilizing tie 218 to cable connector
220. Similarly, cable
tie 219 has a coupling yoke 944 with a pair of parallel flanges 946 with a
pair of aligned holes
948. Arm 904 is inserted between flanges 946, and a lug 950 is inserted in
holes 948 and 920, and
into a nut or other fastener receiver 952.
[00181] Fig. 15E shows a detail of the connection of lower spacer assembly
210 (Fig. 15)
to cables 27 and to large harness 206 by means of connecting structure 214.
The pair of
connecting structures 925 is affixed to cable 27 by engaging loops 244.
Connecting structure 925
is composed of a vertical flange 960 having a connecting flange 962 extending
therefrom and
including a column of lug holes 963. A set of arm support flanges 966 extends
from vertical
flange 960 to which they are welded by an appropriate welding procedure, and
are respectively
connected to respective arms 217 of lower spacer assembly by an appropriate
welding or other
procedure. Arm support flanges 966 are angled from each other and angled where
they engage
respective arms 217 to provide a structurally strong support. Connecting
flange 962 is placed
between the parallel flanges of connecting structure 925 with the holes being
aligned with holes
928 (see Fig. 15B) and lugs 932 and inserted through respective aligned holes
of connecting
flange 962 and holes 928 and through nuts or other fastener receiver 933 (see
Fig. 15A) to secure
connecting structure to cable 27.
[00182] Vertical flange 960 has a finger portion 968 through which extends
a hole 970.
The end of each lead 215 for attaching lower spacer assembly 210 to large
harness 206 has a
coupling yoke 972 composed of parallel flanges 974, 976 through which extend
aligned lug-
receiving holes 978. Yoke 972 is moved so that finger portion 968 is inserted
between flanges
974 and 976 with holes 970 and 978 being aligned. A lug 980 is inserted
through holes 970 and
978, and into a nut or other fastener-receiving means 982.
[00183] It was mentioned earlier that stabilizing ties 218 were connected
to the midpoint of
arms 222. Apparatus for doing this is shown in Fig. 15D. A tie-connecting
flange 984 is attached
to and extends from the midpoint of each of arms 222. Flange 984 has two short
arms 986, each
having a lug-receiving hole 988. Each tie 218 has connecting yoke 944 with
flanges 946 as
discussed above. Yokes 944 from each tie 218 are slipped over an appropriate
arm 986 of flange
984, and a lug is inserted through holes 948 and 988 and tightened in place
with a fastener such as
with a nut.
[00184] Structure for attaching each of the hamesses, spacers and
stabilizers is preferably
composed of the same type of components and subcomponents. This type of
structure is strong,
CA 02875464 2014-12-18
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stable, easy to fabricate and put into use.
[00185] A number of three-sided upper spacer or stabilizer assemblies 260,
virtually
identical to spacer assemblies 210, are located above large harness 206 (as
shown in Fig. 18). The
detailed construction of spacer assemblies 260, and how it is attached to
primary cables 27, is
virtually the same as spacer assemblies 158 and lower spacer assemblies 210.
Spacer assemblies
260, as shown in Fig. 18, is attached to cables 27 by means of connecting
structures 262 at the
intersection of pairs of connected arms of the three arms 264 which form an
equilateral triangle. A
set of lightweight cables 266 (as compared to relatively heavy weight cables
27), extend from
connecting structure 262 to balloon holders 208, which are constructed to hold
them to large
harness 206. Lightweight cables 266 support large harness 206 during assembly
of the launch
system or during maintenance of balloons 164.
[00186] A set of three electric reaction thrusters 800 are respectively
attached to rotatable
support joints 802 at the intersection of respective arms 222, as depicted in
Figs. 18 and 19. Each
thruster 800 comprises a fan 804 which are each mounted in a fan housing 806.
Each housing 806
is pivOtably mounted between a pair of arms 808. Each arm 808 has coaxial
pivot pins 809
extending into housing 806, enabling each housing 806 to pivot about an axis S-
S in the direction
of the arrows T both clockwise and counter clockwise. Arms 808 branch from a
central arm 810,
which is attached to rotatable support joints 802 as discussed above.
Thrusters 800 are gimballed
electric thrusters. Thrusters 800 are pivotable and rotatable, and are
operated to hold the launch
system 1 oriented with respect to the vertical as required. Thrusters 800
compensate for wind
forces and for the partial or total deflation of any balloons 164 until they
can be replaced or
otherwise maintained. The position of large harnesses 206 with respect to the
base of launch
system 1 is controlled by position sensors 812, which could be a global
positioning system (GPS)
for supplying position reference data to the computers controlling the
direction and force of
thrusters 800.
[00187] The following is an explanation of the matter in which balloons 164
(which would
apply to balloons 164A) are attached to the primary cables 27 is shown with
respect to Figs. 15,
16, 17, 18, 20A and 20B. Spacer assembly 260, together with lightweight cables
266 shown in
Fig. 18, located above upper stabilizer 216, has been omitted for clarity in
Fig. 15. Viewing Fig.
15 first, a portion of primary cables 27 is shown, with lower stabilizer 210
and upper stabilizer
216 being provided to stabilize upper harness 206. Three balloons 164 (only
one of which is
shown in solid lines in Fig. 15) are provided for offsetting the self weight
of cable 27, various
stabilizers, and any excess loads applied to cables 27. Depending on their
diameter, balloons 164
may require tubular separators made of the same material as the balloons and
inflated with the
same lighter-than-air gas. In order to keep cables 27 from touching balloons
164 (or balloons
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164A), stabilizing straps or webbing 227 (Fig. 15A) are provided for attaching
balloons 164 to
cable separators such as upper spacer assembly 260 (Fig. 18) to prevent such
contact. Each
stabilizing strap 227 is part of a stabilizer 228 which is connected to each
of cables 27 in the same
manner that other stabilizers are attached to cables 27. Stabilizers 228
further have a connecting
member 229 for holding the respective stabilizing straps 227 in place. The
manner in which the
foregoing is done can be seen in greater detail in Fig. 16, which is a top
view taken in the
direction 16-16 in Fig. 15. It can be seen that each stabilizer 228 is
attached to primary cables 27
within the three intersections of stabilizer 228. Stabilizer 228 is composed
of three respective
arms 234, which collectively intersect to form an equilateral triangle. From
each connecting
member 229, a pair of stabilizing straps 227 forms an angle so that the
respective pairs contact the
respective balloons 164, to which they are nearly tangential. Straps 227 are
each attached to a
balloon 164 by a tangential strap connection 224. Strap connections 224
prevent cables 27 from
contacting balloons 164 (or balloons 164A). Strap connections 224 (Fig. 15)
can advantageously
be an appropriate adhesive, plastic welding or stitching with an adequately
strong thread, for
connecting stabilizing straps 227 to respective balloons 164 (or ilialloons
164A).
[00188] Fig. 17 shows three balloons 164 attached to large harness 206 at
balloon holders
208. Upper stabilizer assembly 216 is shown having its stabilizing cable ties
218 connected to tie
holders 221 on arms 222. Force vectors FF are shown in Fig. 17 extending along
tensioning cable
219, showing tension forces extending from cable connectors 220 to balloon
holders 208.
[00189] A side view of the attachment system is shown in Figs. 20A and 20B.
Each balloon
164 (Fig. 20A) and 164A (Fig. 20B) has light, strong, tension basal connectors
232 connected to a
balloon holder 208 of large harness 206. One or more of connectors 232 may be
tubular to carry
replacement lighter-than-air gas into each balloon 164 to compensate for
leakage. Balloons 164
and 164A are lighter-than-air balloons, so the tensile forces FF are as shown
by the arrows along
connectors 232. Connectors 232 are tangent to the skin of each balloon 164 and
164A. A set of
three or more connectors or stabilizers 228 (Fig. 16) are shown for connecting
the respective
balloons together at several points.
[00190] As explained earlier, tensioning balloons attachment frame 162 has
upper rotating
part 145 and lower rotating part 146 (Figs. 13, 14), which are connected
through ring bearing 149
on the vertical axis for reducing the friction from the rotational movement as
depicted in Fig. 12.
Reaction force thrusters 148 are tangentially attached to the periphery of
upper rotating part 145.
Similarly, reaction force thrusters 178 are attached to the periphery of lower
part 174 of docking
station 166. The propulsive units mounted on upper rotating part 145 and those
mounted on part
174 are used to maintain them non-rotatable. The propulsion units on upper
part 145, in
conjunction with geared rotational drive system 177, assist the rotation of
the lower rotating part
CA 02875464 2014-12-18
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146 relative to upper rotating part 145. Similarly, the propulsive units on
lower part 174, in
conjunction with geared rotational drive system 147 (Figs. 13, 14), assist the
rotation of the upper
rotating part 172. Secondary cables 184 collected in two groups are attached
opposite each other
(180 apart) on lower rotating part 146. Upper hoist 169 is attached to lower
rotating part 146.
Cables 184 connect balloon attachment frame 162 to docking station 166 (Figs.
13, 14) and carry
electrical power as needed. Cables 184 also guide movement of lower hoist
carrier 200, carriage
end gripper 196 and lift ring assembly 182. Cables 184 are long enough to
safely allow a period of
downward acceleration at the local acceleration due to gravity of lower hoist
carrier 200 and items
suspended therefrom, sufficiently long for a,rocket 18 to be disconnected from
its restraint while
in freefall conditions and boosted clear of carriage 20. An additional length
of cables 184 to allow
an additional period of time is also required for the deceleration for the
rest of lower hoist carrier
200 and all items (including loaded or empty carriage 20) suspended therefrom.
An additional
length of cable would permit deceleration of a completely loaded carriage 20
to rest in the event
of a short duration booster misfire.
1001911 As explained above and further discussed below, a means is
required for securing
items of system 1 to the various cables. Fig. 21 shows a cable 240 made of
strands 242 of wire.
Each strand 242 of cable 240 can have looped-out portions or loops 244
extending from the outer
surface of the body of cable 240 for securing items to cabie 240, while
leaving the majority of the
cable's outer surface unobstructed. Each loop 244 extends out from the body of
each cable 240
and returns into the body of cable 240. For example, adaptive connector 247 is
shown in Fig. 22
as discussed in detail hereafter. Adaptive connector 247 has an outstanding
flange 248 having a
series of bolt holes 249 and a further series of bolt holes 250 extending
through a pair of parallel
walls 252 extending in parallel form from a common base 253. Adaptive
connector 247 can be
urged against cable 2'7, with loops 244 slid between parallel walls 252 and
their respective loop
holes 254 in alignment with holes 250. A bolt 256 can be extended through loop
holes 254 and
bolt holes 250 to secure adaptive connector 247 to cable 27 and a nut can be
put on respective
bolts 256 to effect a fin-n connection. A top view is shown in Fig. 23.
Alternatively, parallel walls
255 separated by a spacer 259 as an alternative adaptive connector 257 can be
used, as shown in
the top view of Fig. 24. Cable 27 can be gripped by a pair of traction drive
wheels 26A of
carriages 20 as shown in Fig. 25, rotating in opposite directions 01 and 02.
001921 ln order to use the rocket launch system 1 described thus far,
rockets 18 are loaded
in carriages 20, respectively in one of the apparatus as shown in Fig. 5, and
transported along
pathway 15 with a lateral conveying device 46. Lateral conveying device 46 is
secured to
elevating assembly 60 using the respective tapered alignment pins 142 and
fractional rotation
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twist lock pins 144 and their respective cooperating alignment pin sockets 152
and fractional
rotation twist lock pin sockets 154, as explained with respect to Fig. 9.
Secondary cables 184 and
primary cables 27 are held taut by means of tensioning balloons 160 and
balloons 164,
respectively, with balloons 164 contributing to the tension in primary cables
27. Tension to the
cables below is transferred via tensioning balloons attachment frame 162 and
cable separation and
further tension is achieved via large harnesses 206, spacers 158 and spacer
228 (Figs. 11, 15 and
l 8).
1001931 Each carriage 20 is rotated into alignment with internal carriage
guides 133 and
loaded into lower guide tube 124 (Fig. 8). The upper part of lower guide tube
124 is then tipped
into engagement with the lower part of secondary guide structure 125 (Fig. 10)
until lower guide
tube 124 engages stop 132 to align carriage guides 133 and 138 as discussed
earlier. The traction
drives 26 are then used to drive carriage 20 up cable 27 through docking
station 166 into its upper
part 172 and partially into lift ring assembly 182, which is lowered by use of
hoist 169 so that lift
ring assembly 182 engages with upper part 172 of docking station 166 (Figs.
13, 14). End gripper
196 is lowered and properly attached to the upper end of carriage 20. Lower
hoist assembly 198,
powered by current in secondary cables 184 transferred from cables 27, lifts
carriage 20 further
into engagement 1,vith lift ring assembly 182 such that the combined centers
of gravity of lift ring
assembly 182, carriage 20 and rocket 18 coincide with the pivot axis of lift
ring assembly 182.
Lower hoist 198 thus assists traction drives 26 which engage internal carriage
guides 180A and
180B in lifting carriage 20 upwardly relative to docking station 166. Then
carriage end gripper
196 disengages locking pins 204 from pin lock sockets 32 of carriage 20 and is
lifted minimally
clear by use of lower hoist assembly 198. Lift ring assembly 182 is guided by
secondary cables
184 and supported by tertiary cables 186. Hoist 169 lifts carriage 20 further
until the lower end of
carriage 20 is no longer within the lower part 174 of docking station 166 and
is only within upper
part 172. Geared rotational drive system 147 within lower docking station 166
and geared
rotational drive system 177 with tensioning balloon frame 162 now rotate ail
components in a
coordinated manner between ring bearings 176 and 149 into a direction suitable
for launching
rocket 18. Thrusters 148 and 178 operate simultaneously to keep the lower part
174 of docking
station 166 and, upper ring 145 of tensioning balloons attachment frame 162
from rotating (Fig.
14).
[001941 Hoist 169 next lifts carriage 20 entirely out of engagement with
docking station
166 (carriage 20 holding rocket 18 must be lifted higher and higher according
to their combined
weight) and as high as required into the middle of short tubular ring 183 for
the safe launch of
rocket 18. Rotary drive system 194, in coordination with reversible variable
pitch thrusters 31
extended 90 , rotates short tubular ring 183 with carriage 20 into an
appropriate angle with
respect to the horizontal suitable for launch. Reversible variable pitch
thrusters 31 are being used
CA 02875464 2014-12-18
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to assist rotary drive system 194 and to prevent carriage 20 from oscillating
about horizontal axis
through pins 190. When carriage 20 is at the desired elevation angle for
launch and stable,
reversible variable pitch thrusters 31 are rotated further about thcir hinges
to avoid contact with
hot rocket gases.
[001951 Variations are possible to assist rotary drive system 194. This
includes the
positioning and stabilizing of carriage 20 in lift ring assembly 182, and in
particular to prevent the
oscillation of carriage 20 about pivot pins 190. Referring to Figs. 13B-13C,
there can be provided
at both ends of carriage 20 reversible variable pitch thruster 31 and a pair
of accompanying hub
motors 822. Each thruster 31 and hub motor 822 can be housed in one end of
carriage 20 beneath
an end cover 830. Each thruster 31 has a set of rotatable blades 826 that are
mounted in a
pivotable thruster mounting 828 at both ends of carriage 20. Each mounting 828
is mounted on a
hinge assembly 829 and is movable between a rest position (shown in dotted
lines in Fig. 13C and
an active position parallel with the longitudinal axis of carriage 20 (shown
in Fig. 13C in solid
lines) by means of a hydraulic actuator 832, which pivots about an actuator
pivot 834. When
thrusters 31 are in their active position, an airstream is created as shown by
arrows U. This
prevents oscillation of carriage 20. Hub motors 822 are reversible since the
airstream can go in
both directions. Likewise, the pitch of blades 826 is variable to vary with
variance of the ambient
air in which blades 826 are rotating. However, when the engine of rocket 18
ignites, thrusters 31
can be inoved at an obtuse angle as shown in dotted lines at the left-hand
part of Fig. 13C to avoid
the short duration booster exhaust. The upper end of thruster 31 is also moved
to its obtuse
position to enable the loading of a rocket 18 into carriage 20. It should be
noted that the inside of
carriage 20 has continuous pressure-and-heat resistant tube 836 running from
end-to-end to
contain a rocket 18 therein. A set of three or more centering supports 840
maintain the centering
of each reversible, variable pitch thruster 31.
[00196] The upper end of hoist cable 202 (Fig. 14) is fed out from upper
hoist 168 and
reversible traction drives 193 of lift ring assembly 182 begin to drive
downwards, while in
operative engagement with secondary cables 184. Hoist cable 202 unreels and
moves lift ring
assembly 182, carriage 20, rocket 18 and all other components supported by
cable 202
downwards assisted by drives 193 to overcome friction and air resistance, so
that they are in
freefall at an acceleration of lg, and rocket 18 becomes weightless with
respect to carriage 20.
There is a slight friction maintained in upper hoist 168 to maintain control
during freefall, and to
avoid any slack and any uncontrolled unwinding of cable 202. Prior to
freefall, retractable end
covers 30 (Figs. 9, 9C, 13, 13A) of carriage 20 are opened (or end covers 830
shown in Fig. 13C
are opened). Retractable arms 34 or 35 (Fig. 26) inside of carriage 20, which
had been holding
rocket 18 in carriage 20, are retracted (as discussed below), and the short
duration booster rocket
CA 02875464 2014-12-18
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motor of rocket 18 is ignited to drive rocket 18 out of carriage 20. The short
duration booster
rocket motor only operates within the heat and pressure resistant confines of
carriage 20 to
prevent damage to launching system 1.
[00197] After rocket 18 has travelled sufficiently far on its ballistic
path, its main motors
can be safely ignited as required to avoid damage to launching system 1. The
feeding out of the
cables 202 from upper hoist 168 (Fig. 12) is gradually stopped while
reversible traction drives 193
of lift ring assembly 182 (Fig. 13) are operated in a braking mode to prevent
the further freefalling
of carriage 20, lower hoist carrier 200, carriage end gripper 196 and lift
ring assembly 182 (Figs.
12, 13, 14). Reversible variable pitch thrusters 31 (Fig. 13C) may then be
used to assist the
rotation of carriage 20 into a vertical position before they are retracted
into the ends of carriage 20
and may be used to purge any exhaust gases from the interior of said carriage
before closing the
weather covers 30.
[00198] Short tubular ring 183, of lift ring assembly 182 with empty
carriage 20, having
been rotated into the vertical position (in preparation for rotation about the
vertical axis, since the
rotational moment of inertia is lowest when carriage 20 is in the vertical
position), is then and
lowered by means of upper hoist 168 in engagement with upper part 172 of
docking station 166,
shown in Figs. 13 and 14. Carriage 20 and carriage end gripper 196 may then be
brought together
to lock carriage 20 to carriage end gripper 196 before carriage 20 is lowered
into engagement with
upper part 172 if additional support or guidance is needed. The lower end of
carriage 20 is then
lowered into engagement with upper part 172 of docking station 166. Lower part
146 (Fig. 14) of
tensioning balloons attachment frame 162 and upper part 172 of docking station
166 are next
rotated so that the internal carriage guides 188 of lift ring assembly 182
(Fig. 13, 14) and internal
carriage guides 180 of upper part 172 come into alignment with cables 27 of
docking station 166
(Fig. 13). Hoist 168 then lowers carriage end gripper 196 to the top of lift
ring assembly 182
(Figs. 12, 13, 14) and releases carriage 20. Lift ring assembly 182 also
disengages from carriage
20.
[00199] Carriage 20 quickly drives down the cableway path 170 (Fig. 11)
formed = by
primary cables 27 using regenerative braking to keep the downward speed of
carriage 20 to a
manageable level. The power returned to primary cables 27 in-this and other
launching stations is
transferred to another launch system to supplement or replace the power
required for the elevation
of another carriage 20 up its cableway path 170. A minimum group of four
active launch systems
is envisaged with a fifth acting as a ready spare used for light duties such
as tourism or high
altitude skydiving utilizing special lightweight carriages until an active
launcher requires
maintenance or a higher net rocket launcher rate is needed. A combined launch
rate of once per
hour is believed to be feasible.
CA 02875464 2014-12-18
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[00200] After empty carriage 20 re-enters secondary guide structure 125
(Figs. 1A, 2, 8, 10
and 11), it is further lowered until carriage 20 disengages from secondary
guide structure 125 and
becomes centered in lower guide tube 124 at the point where the combined
centers of gravity of
carriage 20 and lower guide tube 124 coincide with the rotational axis of
lower guide tube 124.
Lower guide tube 124 is then returned to the vertical position and carriage 20
is lowered onto an
appropriately aligned lateral carrying device 46 atop elevating assembly 60.
Lateral conveying
device 46 returns empty carriage 20 to blast resistant assembly bay 10 for
reloading or to storage
racks 7 for replacement and refurbishing. Another pre-assembled rocket 18,
carriage 20 and
lateral carrying device 46 can be loaded into system 1, and the next rocket 18
launched as
described above.
[00201] One possible construction of a retractable arm is retractable arm
34 in the direction
of arrow V for holding rocket 18 in carriage 20 as shown in Fig. 26. Rocket 18
has at least six
equally spaced adjustable slots 300 for receiving retractable arms 34, there
being one arm 34 for
each slot 300.
[00202] Referring next to Fig. 27, alternate, different retractable arms 35
may be provided.
Each retractable arm 35 has a head member 302 for entering one of slots 300,
and a base member
304 from which extend opposing, coaxial pivot pins 306. A stem 308
interconnects head member
302 and base member 304, and strengthening webs or braces 310 extend between
base member
304 and stem 308. Carriage 20 has an interior, blast resistant tube 312 having
a cavity 314. Tube
312 has a pair of protecting doors 316 mounted on hinges 318 which can be
positioned to close
part of cavity 314 (as indicated by the arrows W) or pivot outwardly to open
part of cavity 314 as
shown in Fig. 27. Tube 312 also has a cavity-covering end door 320. Door 320
may have an
airflow deflector 322 for protecting doors 316, 320 and cavity 314, a
reinforcing spine tension
member 324 and a pin holder 326 holding coaxial pivot pins 328 for entering
pivot sockets 331 on
approximate sides of side walls 332 defining part of cavity 314. Door 320
pivots on pins 328
between open and closed positions. Walls 332 also have pivot sockets 334 for
receiving pins 306
of retractable arm 35.
[00203] Cavity cover door 320 further has a hydraulically retractable pin
336 for moving in
and out of a socket 338 located in an arm 340 of door 320, and a hole 339 in
base member 304.
Door 320 also has parallel legs 342 with aligned holes 344. Stem 308 of
retractable arm 35 has an
upstanding portion 346 with a slot 348 extending longitudinally in stem 308.
Portion 346 extends
between legs 342, and a slider pin 350 extends through slot 348 and into each
hole 344 to couple
retractable arm 308 to cavity cover door 320. A hydraulic arm 352 has legs 354
with aligned holes
360 for going between a pair of legs 362 at an end floor 364 of cavity 314,
legs 362 having
aligned holes 366, and legs 354 are held in place by a pin 356 extending
through holes 360 and
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366. Another pair of parallel legs 368 extends from a shaft 369 extending
generally forwardly
from arm 352, and a pair of aligned holes 370 receive a pin 371. Doors 316 are
opened and closed
by hydraulic or electro-mechanical means, coordinated with door 320.
[00204] The foregoing arrangement locks doors 316 and 320, which are shown
in Fig. 27 in
their open position, and head members 302 of each retractable arm 35 remain in
the respective
slots 300 in rocket 18. When rocket 18 is in freefall with carriage 20 and
becomes weightless with
respect to carriage 20, arms 35 are rapidly retracted into their respective
cavities 314 along with
the rest of the assembly operating with arms 35, and doors 316 and 320 are
closed just prior to
ignition of booster rocket motor of rocket 18. Each rocket 18 can have small
sets of wheels 372 to
keep rocket 18 centered in tube 312 during launch in the event the line of
thrust is not exactly
coaxial with the internal tube of carriage 20 or does not pass through the
rocket's center of mass.
[00205] Another version of the invention, in addition to launching rockets,
can be used if a
telescope is to be lifted to the top of the unit. Referring to Figs. 28 and
28A, a telescope holding
system 373 is shown. Fig. 28A shows balloon 160 in reduced form. The
components related to
the telescope are discussed below. System 1 has three primary cables 27 which
carry electric
power, and are attached to a docking station 374. Docking station 374 has an
upper part 376
which is rotatable in the direction of arrow X relative to a lower part 378
using rotational drive
system 379. Referring to Figs. 28B and 28C, rotational drive system 147
rotates upper part 376
and lower part 378 relative to each other by means of a ring bearing 850
having an inverted L-
shaped member 852 in cross section, with sets of ball bearings 854 and 856 in
tracks 857, 858 and
859, 860 in upper part 376 and L-shaped member 852, and lower part 378 and L-
shaped member
852, respectively.
[00206] The upper ends of cables 27 are held fast as shown. One cable 27A
extends at an
angle through an opening 862 in lower part 378 and an appropriate clamping
mechanism 864 for
holding cable 27A fast. A second one of cables 27 is shown as cable 27B, and
it is held fast by an
appropriate means to a flange 866, as further shown in Fig. 28C. The third one
of cables 27 is
similarly held fast. A motor 868 rotates a gear 870. Gear 870 is sequentially
connected to teeth
872 of upper part 376 to effect the foregoing rotation as shown by arrow Y. A
protective housing
could enclose motor 868 and gear 870.
[00207] Three or more reaction thrusters 380 can be used, and they offset
the relative
rotation of parts 390 and 378 which are kept stationary when the alternate
launching system
depicted in Fig. 28 is used to launch rockets. Similar to other docking
stations, a ring bearing 377
and rotational drive system 147 are included between upper and lower parts
376, 378 of docking
station 374. Secondary cables 184 also carry electrical power for operating
the electrically
powered components. It could be a two cable direct current apparatus or a four
cable, three-phase
CA 02875464 2014-12-18
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apparatus.
[002981 A lift ring 382 drives up or down in the direction shown by arrows
Z on cables
184. Lift ring 382 includes reversible traction drives 386, and a structure
387 for holding carriage
20 which is able to pivot in the direction indicated by arrow AA and a rotary
drive 381 to change
the angle of lift ring 382 and carriage 20. An upper docking station 388 has
an upper part 390
normally held stationary and a lower part 392, being rotatable in directions
shown by arrows BB
about a vertical axis using rotary drive 381. A ring bearing 394 reduces the
friction from such
rotation. A minimum set of three reaction force thrusters 397 counters the
tendency of upper parts
390 to rotate about the vertical axis.
1002091 A rigid elevator shaft or elevator tube 396 may carry special
carriages 398 each
having a telescope CC built within, to a top mount 399. A special lightweight
carriage or carriages
20A could also be used for transporting carriage 20 up elevator tube 396 to
mount 399 after
transfer from lift ring 382. A set of electricity carrying cables or rails
could be mounted on the
insidc of elevator tube 396 which the wheels of carriages 398 or 20A would
engage and also
receive electric power (as did wheels of traction drives 26 which engaged
cables 27), to enable the
transport of carriage 20A up and down the inside of elevator tube 396.
Balloon(s) 160 are attached
to or surround elevator tube 396 as described earlier to provide sufficient
tension to cables 184 to
enable the transport of lift ring 382 with special carriage 398 holding
telescope CC therein, as
well as to support the cables themselves and the apparatus attached to the
cables.
[002101 Telescope top mount 399 includes a turret-like platform 402 upon
which is
disposed a rotatable turntable 404, which rotates with respect to stationary
upper part 390. A
telescope-receiving hole 405 extends through platform 402 and turntable 404 as
shown in Figs.
28A and 29. Mounting walls 406 extend from turntable 404. A telescope-holding
structure or ring
408 clamps special carriage 398 with telescope CC therein, with the center of
gravity of carriage
398 disposed in the center of ring 408 which acts in the same manner as lift
ring assembly 182 but
without traction drives. As shown in detail in Fig. 29, ring 408 has coaxial
pivot pins 410 which
extend into sockets 412 of mounting walls 406. Mounting walls 406, ring 408
and pivot pins 410
for a telescopic tilting structure 411 are provided. Therefore, carriage 398
and telescope CC
mounted within it can be tilted in elevation as desired, and the rotation in
azimuth shown by arrow
DD of turntable 404 directs carriage 398 and telescope CC included in any
desired direction.
Turntable 404 and platform 402 may be made independently rotatable in the
respective opposite
directions =shown by arrows HH and U (Figs. 28A, 29) with respect to elevator
tube 396. This
rotation is effected by means of a rotary drive 383, similar to drive 381.
Platform 402 may have
radially adjustable weights to make its rotational moment of inertia equal to
the rotational
moments of inertia of the assembly of turntable 404 and parts above it so that
when they are
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rotated in opposite directions no net torque is applied to elevator tube 396
as turntable 404 and
parts above it are rotated.
[00211] Rocket launch system 1 can be used for a variety of purposes. For
example, it
could be used to launch a single man or basic rocket 601 which has a steerable
motor 603 as
shown in Fig. 30, which is movable as indicated by arrows EE to steer rocket
601. A person or
occupant GG is shown wearing a fluid filled launch or re-entry suit 605 with
joints 607 locked in
an optimal aerodynamic upright position for launch and locked feet first onto
the top of rocket
601, for resisting the g-force effects of the firing of rocket 18 during
launch. Suit 605 detaches
from rocket 601 as desired after rocket 601 stops operating and the joints of
the suit are unlocked,
permitting the occupant GG to move freely. If the suit is to be used for re-
entry, a portion of the
fluid surrounding the occupant GG can be pumped through porous pads to cool by
evaporation the
exterior of re-entry suit 605 upon re-entry, feet first. (The same pumping
operation and the
cooling effect would apply at launch as well.) Rocket 601 with occupant GG in
suit 605 mounted
on top, should afford occupant GG an excellent view during the launch phase.
An aerodynamic
fairing around suit 605 may not be required, unless when so configured, and
the set of joints 607
are locked in position, aerodynamic drag is still higher than necessary for
optimal launch.
[00212] Fig. 31 shows a possible method for transporting tourists in suits
605 or materials
in rigid pods 608 releasably clamped to a core rocket 604. Main rocket 601
ceases its controlled
launch at a period after its launch. Core rocket 604 is releasable from main
rocket 601 upon
cessation of the controlled launch of main rocket 601. A windshield 609 can be
used to protect
tourists in suits 605 or pods 608 from high velocity air as rocket 601
penetrates the atmosphere on
its way to space where the suits 605 or pods 608 may be released in the
direction indicated by
arrows B. Core rocket 604 may have a set of turntable fins 602 which are
turned in the directions
KK by the directional control system to steer rocket 601.
[00213] Fig. 32 shows an alternate pod 610 with a sled-like re-entry frame
616. Occupant
GG wears launch or re-entry suit 605. Sled-like re-entry frame 616 includes
steering fins 619, and
an aero-spike 611. Aero-spike 611 has an extendable antenna-like configuration
with a disc 613
serving as a forward shocicwave initiator to yield a shockwave 615 for
reducing aerodynamic
heating of suit 605.
[00214] In Fig. 33, re-entry suit 605 with person GG is shown fitted into a
more rocket-like
shaped frame 617 with directional steering fins 618 and aero-spike 611. Frame
617 has disk 613
as discussed with respect to Fig. 32. A guidance equipment and storage
compartment may be
located in the aft interior frame 617.
[00215] An appropriate space suit 605 is shown on person GG in Figs. 34 and
35, also
serving to accommodate g-force effects. Space suit 605 enables occupant GG to
survive, remain
CA 02875464 2014-12-18
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conscious and be able to remain active while in an upright posture in a high
acceleration
environment. For extended operations, this is achieved by immersing the
occupant in a fluid of
approximately the same density as the body, within a rigid suit with external
electro-mechanical
or hydraulic, servo-assisted, constant volume joints. Space suit 605 has a
helmet 650 (Figs. 34,
34A, 34B, 36) surrounding the head of person GG, and a rigid outer shell 648.
An inner suit 651
lies close to person GG, and an internal face mask 653 with a visor 655 is
sealed to inner suit 651.
A nontoxic fluid 656 (Figs. 34, 34A-34B) such as water fills the space between
rigid outer shell
648 and inner suit 651. If fluid 656 is heated to a comfortable temperature,
inner suit 651 may be
omitted. There is a double seal 654 between inner suit 651 and face mask 653.
Inner suit 651
could be skin tight around person GG, and face mask 653 could be ventilated to
or from an air
supply via an air supply tube 661. A leakage canal 652 is provided on face
mask 653 of space suit
605 for draining water if there is leakage into the space between the double
seals surrounding the
face of person 00. Water or other appropriate nontoxic fluid 656 fills the
space between inner
suit 651 and outer shell 648, and face mask 653 and visor 655 as shown in
Figs. 34, 34A and 34B.
Person GG in space suit 605 can turn his head within helmet 650 while
suspended in water 656.
Space snit 605 is of rigid lightweight construction; however, volumetric
airflow sensors in face
mask 653 or visor 655 could be provided to direct a hydraulic or electro-
mechanical drive piston
(explained below) to move in and out to match the change of volume due to
breathing.
Additionally, in order to match the breathing rate, that is, the change of
volume divided by the
change in time, pressure sensors at various places (particularly near the
chest) in space suit 605
keep the liquid pressure constant by directing the piston in and out. The use
of external high
pressure hydraulic power assistance to permit person GG to move about freely
in suit 605 in high
acceleration environments such as exist during launch or re-entry avoids the
possibility of water
or other hydraulic fluid used to activate the joints of the suit from escaping
into the suit's interior
which could crush occupant GG.
[00216] With respect to the piston, reference is also made to Fig. 35.
Here, space suit 605
has water (or nontoxic fluid approximating the density of the human body) 656
filling the suit
around person GO, and a piston 657 moves in and out of a cylinder 660, powered
by high
pressure hydraulic fluid or direct actuation of piston 657 by electro-
mechanical apparatus to vary
the volume in suit 605 as required for normal respiration.
[00217] The rigid outer shell 648 is typical of the construction of suit
605 depicted in Fig.
34 and is shown in Fig. 36. Rigid outer shell 648 of suit 605 includes a pair
of rigid sleeves, each
containing internal sleeves 664 (only one is shown) each of which is made from
open, elastic
webbing or a soft, open pore foam or webbing and a pair of rigid legs each
having internal legs of
the same construction as internal sleeves 664. The -internal sleeves and
internal legs will
CA 02875464 2014-12-18
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hereinafter be referred to as "internal sleeves." The pores should be large
enough so as not to
=
impede significantly the flow of water through sleeve 664. Sleeve 664 is held
centered within suit
605 by means of weak elastic tendons 668 attached at one end to suit 605,
which extend across
sleeve 664 and are attached to, and tangent to sleeve 664 to which they are
attached at the other
end. The tensions in elastic tendons 668 are sensed and used to provide
feedback to direct the
powered joints of suit 605 to mirror the motions of occupant GG, keeping him
centered within the
suit. An occupant GG merely slips into suit 605 and slides his or her entire
body into typical
sleeve 664. Suit 605 is a practical and efficient space suit to be worn by a
person GG on rocket
601 or within rocket 18, particularly during the launch, boost and re-entry
phases of flight. Outer
shell 648 could have an ablative exterior material with insulation or heat
resistant thermal
insulation.
[00218] Other versions of a rocket are shown in Figs. 37, 38, 38A and 39. A
rocket 700 has
an aerospace plane 702 with deployed, and folded lift and directional control
structures 704
attached to the body shown in Figs. 37, 38 and 38A, and foldable in the
directions shown by
arrows LL and MM A lifting body type re-entry vehicle 706 is shown in its
folded launch
configuration in Fig. 38 with lift and directional control structures 704 in
folded condition. Lifting
body type control re-entry vehicle 706 with lift and directional control
structures 704 foldable in
the further direction indicated by arrows NN is shown in Fig. 38A in the
folded and unfolded
configurations. Rocket 700 is primarily a military version of rocket 18.
[00219] Referring to Fig. 39, a more typical rocket 720 is shown. Rocket
720 includes a
satellite or other payload 722 which is protected during launch and flight by
a pair of disposable
aerodynamic shells 724. After rocket 720 has left the atmosphere, shells 724
are automatically
detached in the directions indicated by arrows PP and preferably fall back to
earth and the satellite
or other payload 722 goes into space. Rocket 720 is primarily a commercial
version of rocket 18.
[00220] The preferred embodiment described above can be achieved using
presently
available materials and products. The typical carriage, loaded with a rocket,
can be estimated to
weigh 80 tons although greater weights are possible. Each cable must be strong
and electrically
conductive. It should further be wear resistant to withstand the travelling of
traction wheels up
and down the cables. Thus, cables 27 and 184 could have a steel exterior, with
intermediary
portion of aluminum, and a steel core. The cables could be multi-stranded with
copper and steel
strands and copper coated steel strands or other suitable construction. For a
70 ton lift, the cables
should be about 2/3 inch in diameter. Each of three cables could have 1.25
inch diameter, and the
secondary cables should each have a diameter of one inch.
[00221] As noted earlier, the weight of the cables is advantageously offset
periodically.
Steel cables having a diameter of 1.125 inches weigh about 2.03 pounds per
foot. A factor of
CA 02875464 2014-12-18
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safety of at least five should be used. A one inch diameter cable holds 120
tons at its breaking
point.
[00222] The preferred gas for the balloons should be hydrogen, which is
much more
buoyant than helium and may be generated from water, while limited supplies of
helium are
primarily mined from natural gas wells. However, safety is an important
factor. The higher in the
atmosphere the balloons go, the risk of a lightning strike increases.
Therefore, the turntable, lifting
assembly and components above all should be insulated from the earth,
electrically charged to the
same electric potential as the high altitude atmosphere to avoid attracting
lightning, and the
electrical power supply inductively connected. The insulating parts of the
rocket launch system
could advantageously be made from ceramics or glasses.
[00223] The skin for the balloons should be light, strong and ultraviolet
(UV) light
resistant. There has been ample work done in such skins from the design and
operation of
dirigibles and other balloons recently.
[00224] The advantages of the present inventive rocket launching system
over those
presently in use are quite apparent. The first stage of the Saturn V Rockets
launched by NASA
consumed 203,000 US gallons of RP-1 (refined kerosene) and 331,000 US gallons
of liquid
oxygen (LOX) in a period of 2.5 minutes. The present invention could have
greatly reduced the
amount of propellants to loft the same payload by lifting numerous smaller
rockets using the
electrically powered carriages with an equivalent payload up the balloon
supported cables to a
desired height prior to launch. The present state of the art uses a tremendous
amount of non-
recoverable fossil fuel based energy. For example, the Virgin Galactic White
Knight Mothership
uses tons of JET-A-1 kerosene fuel to reach its launch altitude for the Space
Ship Two which uses
a form of rubber with a liquid oxidizer, and yields a black sooty exhaust.
Solid rocket boosters
often leave fluorine and chlorine compounds and partially-burnt hydrocarbons
amongst other
dangerous residues in their exhaust. All of these exhausts and residues
pollute the atmosphere. On
the other hand, the energy used in lifting the carriages in the preferred form
of the present
invention is derived from renewable sources and a significant portion is
recovered when the
traction drives switch to their regenerative mode when the carriage goes back
down the cableway.
[00225] Furthermore, the present invention will reduce the cost of space
flight sufficiently
to permit the removal of debris in the orbit around our planet and even permit
the construction of
an orbital shipyard. A vivid example of the hazards of orbital debris in space
was the collision of
a non-operational Russian Cosmos 2251 communications satellite with a U.S.-
based mobile
telephony satellite owned by Iridium on February 11, 2b08. Each satellite was
travelling at an
orbital speed of 17,500 miles per hour. The debris from this collision was
estimated to amount to
500 pieces. NASA has said that this debris from the collision has elevated the
risk of damage to
CA 02875464 2014-12-18
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the International Space Station. The International Association for the
Advancement of Space
Safety has proposed the mandatory removal of non-operating satellites.
[00226] The present invention thus includes a set of cables supported by
lighter-than-air
balloons, which can be used for a variety of purposes in a very effective and
efficient manner.
When used to launch rockets, the amount of fuel required at launch is
dramatically reduced since
the rockets are transported into the upper atmosphere before their engines are
operated. The
rockets can be used for a variety of purposes, and due to the reduced energy
expenditure and the
resulting cost reduction, such uses as recreational sports using rockets,
parachutes, small .jet
engines, or other apparatus could be economically feasible. Likewise,
facilities for servicing
satellites become more feasible and economic. Uses for high altitude platforms
such as for
telescopes could be a tremendous benefit to scientists.
[00227] In the preferred embodiment discussed above, three cables were
provided for
three-phase electrical power. It is likely each cable should transmit exactly
one third of
electricity. In the event this cannot be done or in the event there is a
possibility it can be
accomplished during use of the rocket launch system according to the
invention, structure should
be provided for either having a neutral line or else a ground to get the
necessary electrical balance
amongst each of the three cables.
[00228] The present invention has many uses in addition to those described
above. There is
a tremendous amount of debris orbiting the earth from the many rockets driven
into space. NASA
has estimated that in 2009, there are about 14,000 objects which are being
tracked by the U.S.
Space Surveillance Network. Many of these objects threaten other devices which
may pass
through the respective orbits of these objects, since collisions could cause
considerable damage.
The present invention could be used to place debris catchers in 'orbits for
recovering and de-
orbiting such debris in an economical and safe manner or recycling such items
as may be reusable
into useful structures in orbit.
[00229] The cables discussed herein were described as being of the general
type of rope
composed of twisted strands of metal and shown as twisted into a helix. These
are wire ropes
which are electrically conductive, and are similar to those used on cable
cars, funiculars and aerial
lifts. Different variations in the cables have been discussed as well.
However, the term "cable" is
not intended to be restricted to wire ropes. Cables could also be rods of
different sorts, coming in
single lengths, joined by various types of welding, or jn a series of smaller
links which are
coupled together to yield the desired length. The important feature of
whatever cable is used
according to the invention is that it be strong, electrically conductive and
able to take the stresses
and strains which would exist at elevated altitudes for transporting rocket
transporting devices and
other apparatus as discussed herein. These rods or other types of cables may
be modified in
CA 02875464 2014-12-18
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different respects, such as, for example, to modify the surface or
configuration of the surface of
the rods or other cables so that the system would operate more effectively and
more efficiently
when the rods or other cables cooperate with the traction drives of the
respective rocket
transporting devices. Such rods could have a cylindrical cross section or
other cross sections
depending, for example, on the nature of the traction drives used therewith.
Referring to Figs. 40
and 41, a rod 990 is shown connecting flanges 992 attached at joints 994.
Flanges have
attachment holes 996. As required to attach spacers on other structures to the
side of the rods to
allow bolted or other connections may be attached by means of bonding, solid
state or other forms
of welding (e.g. friction welding, explosive welding, brazing, etc.) or
joining as deemed fit. The
rods could be modified in other ways depending on such factors as the nature
of the linkage of the
respective rods, the electric conductivity of the rods, the safety of the rods
and the like.
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