Note : Les descriptions sont présentées dans la langue officielle dans laquelle elles ont été soumises.
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Docket No: 663-003
AIRCRAFT SHELTER
BACKGROUND
[0001) Field of the invention:
[0002) The present invention relates to an aircraft shelter for protecting an
aircraft from
adverse weather, and more particularly, to an aircraft shelter that is
adaptable for
protecting low-wing airplanes, high-wing airplanes, and helicopters. The
aircraft shelter
can be manufactured for modular or portable assembly and presents significant
manufacturing and installation and use advantages over the prior art.
[0003) Background of the invention:
[0004) There has long been a need to protect parked small aircraft from
adverse weather
such as, for example, strong sunlight, strong wind, heavy rain, heavy snow,
and hail.
Typically, permanent or semi-permanent hangars are used to protect aircraft
parked on an
airfield. However, hangar space is limited and expensive to rent or purchase.
Similar
protection scenarios and requirements exist for both high- and low-fixed wing
aircraft, as
well as helicopters. A variety of semi-permanent shelters have been developed
to offer
some protection from adverse weather such as disclosed, for example, in US
Patents
5,390,688 and 7,089,951 for protecting airplanes. Other types of semi-
permanent shelters
have been specifically developed for protecting helicopters such as disclosed,
for example,
in US Patent 6,749,151 providing only limited protection and US Patent
8,336,807
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providing a complex and expensive clamshell case for encapsulating the
helicopter.
[0005) Unfortunately, these shelters still have a significant footprint and
are most often
attached to a fixed or poured concrete footing or the like -therefore, they
are viewed by
airports as hangars. This type of zoning or characterization makes these
shelters more
difficult and costly to site, as well as being complicated in cost and labour
for installation
or manufacture. The need for a fixed footing or foundation also makes the
economics of
assembling or installing an aircraft shelter cost prohibitive in many smaller
locations or
environs.
[0006] Many of these aircraft shelters are not capable of withstanding strong
wind and heavy
snow loads as exist in environments such as the North American plains - in
these
environments it would be desirable to cover and protect the exterior and
control surfaces of
aircraft parked in an outdoors or semi-protected scenario where full hangar
protection is not
available, but the need to withstand the elements is a complicating factor in
design of such an
aircraft shelter. Therefore, a large number of parked light aircraft are
simply tied down
outside and either completely exposed to adverse weather, or possibly have
only some
surfaces ¨ canopy, cowling, wings, and/or tail - covered using separate covers
made of a
fabric material. Unfortunately, the more covers that are used to protect the
aircraft, the
more time and effort is required for installing and removing them. These
partial covers
protect from sun but largely do not protect against hail, heavy snow, or wind.
In addition
to sun protection, it is desirable to provide an aircraft shelter for
protecting an aircraft that
is capable of withstanding strong wind, heavy rain, heavy snow, and hail.
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[0007] It would be desirable to provide an aircraft shelter for protecting an
aircraft that
covers all or a substantial portion of the aircraft and has a substantially
small footprint. If
it were possible to use a semi-portable or portable aircraft shelter, it is
felt that this would
be well accepted in the marketplace. Particularly if the need for individual
fabric covers
were alleviated it is believed this would provide significant benefit.
[0008] It is also desirable to provide an aircraft shelter that is easily
opened and closed to
enable entry/exit of the aircraft. One of the issues with many of the prior
art aircraft shelters
are that even where they do exist in a reasonably straightforward to erect
fashion, the
application of multiple covers to the surfaces of the aircraft, often applied
during the
inclement weather, makes it more difficult and time consuming, and less
attractive to use.
BRIEF SUMMARY
[0009] The object of the present invention is to provide an aircraft shelter
for protecting an
aircraft which has a substantially small footprint. Another object of the
present invention is
to provide an aircraft shelter to provide a shelter for protecting an aircraft
that is capable of
withstanding strong wind, heavy rain, heavy snow, and hail.
[0010] Another object of the present invention is to provide an aircraft
shelter that is easily
opened and closed to enable entry/exit of an aircraft from a defined shelter
cavity. The
aircraft shelter might also be locked with the aircraft located therein, for
the purpose of
minimizing the possibility of theft of the stored aircraft.
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[0011] Another object of the present invention is to provide an aircraft
shelter that is
adaptable for protecting multiple types of aircraft including low-wing
airplanes, high-wing
airplanes, and helicopters.
[0012] The aircraft shelter includes a rear shelter section defining a
rearward shelter
cavity, and a front shelter section placed ahead of the forward edge of the
rear shelter
section and defining a forward shelter cavity. The rear shelter section may
include side
wall portions engaging the ground, a top defining the apex of the rearward
shelter cavity,
and/or a forward edge which is positioned in proximity to a forwardmost
portion of the rear
aircraft section when the aircraft is sheltered therein.
[0013] The front shelter section is moveable between a closed position for
sheltering the
aircraft and an open position for enabling entry and exit of the aircraft from
the aircraft
shelter. The aircraft shelter might be locked in the closed position, for the
purpose of
minimizing the possibility of theft of the stored aircraft.
[0014] The front shelter section comprises at least one front support beam
movably
mounted to the forward edge of the rear shelter section in proximity to the
top thereof
such that in the closed position the at least one front support beam is
positioned above
the aircraft, and is supported at its at least one distal end by at least one
front support
post extending downwardly to the ground, and/or a flexible fabric front
section cover
extending forward from the forward edge of the rear shelter section.
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[0015] The at least one front support beam may comprise two beams, namely a
left
front support beam and a right front support beam, and the at least one front
support
post may include a left front support post connected to the left front support
beam and a
right front support post connected to the right front support beam. The left
front
support post may be oriented downward to the ground to the left-hand side of
the
aircraft and the right front support post may be oriented downward to the
ground to the
right-hand side of the aircraft. In the closed position the left front support
beam and the
right front support beam are substantially rigidly connected to each other. As
well, in
some embodiments, in the closed position the left front support beam and the
right
front support beam are disposed in close proximity to each other [permitting
them to
optionally be locked together]. In some embodiments, each of the left front
support
beam and the right front support beam are rotatably moveable - in a
substantially
vertical direction and a substantially horizontal direction, or otherwise. In
the closed
position the left front support beam and the right front support beam may be
positioned
above the front aircraft section of the aircraft.
[0016] At least one of the left front support beam and the right front support
beam can
have at least one curved section adapted for surrounding a portion of the
aircraft with
the aircraft shelter in the closed position (where the aircraft is a
helicopter).
[0017] A front section cover, made of flexible and element-proof fabric, is
mounted to
the left front support beam and the right front support beam, and/or the left
front support
post and the right front support post. In some cases the front section cover
comprises a
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left front section cover and a right front section cover.
[0018] In cases where the aircraft to be sheltered is a fixed wing aircraft
having a left
wing and a right wing, the forwardmost portion of the rear aircraft section
may include a
horizontal beam extending rearward of the trailing edge of the left wing and
another
rearward of the right wing of the aircraft. Such an aircraft shelter may
further include a
left wing shelter section and a right wing shelter section extending outwards
and forwards
from the forward edge of the rear shelter section and the front shelter
section, for
sheltering the left wing and the right wing of the aircraft when the aircraft
shelter is in
the closed position. The left wing shelter section and the right wing shelter
section
may include a left wing cover and a right wing cover each made of flexible
fabric, for
covering the left wing and the right wing of the aircraft.
[0019] The left wing shelter section may further include a rearward left wing
beam
laterally extending substantially perpendicularly outwards from the forward
edge of the
rear shelter section, for supporting the left wing cover. Similarly, a right
wing shelter
section may further include a rearward right wing beam laterally extending
substantially
perpendicular outwards from the forward edge of the rear shelter section, for
supporting
the right wing cover. The rearward left wing beam and the rearward right wing
beam will
be positioned above the ground approximately equal or higher in height than
the
forwardmost portion of the rear aircraft section, being behind the trailing
edges of the left
wing and the right wing. The rearward left wing beam and the rearward right
wing beam
can be adjustable in length - telescopically for example, and adjustable in
height of
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attachment to the remainder of the aircraft shelter.
[0020] The left wing shelter section and the right wing shelter section might
each include a
forward left wing beam and a forward right wing beam, respectively, to further
enhance support
for the left wing cover and the right wing cover in front of the leading edge
of the left wing and
right wing of the aircraft. The forward left wing beam and the forward right
wing beam are
positioned above the left wing and the right wing of the aircraft and in
proximity thereto.
[0021] In some embodiments, the aircraft shelter may further include a left
cantilever beam
mounted to the rear shelter section and extending forward therefrom to support
an inner end
of the forward left wing beam and/or a right cantilever beam mounted to the
rear shelter
section and extending forward therefrom to support an inner end of the forward
right wing
beam. The left cantilever beam and the right cantilever beam may be mounted to
the rear
shelter section at matching or different distances above the ground.
[0022] Some embodiments of the aircraft shelter of the present invention may
also include
a left wing beam support structure for supporting an outer end of the forward
left wing
beam and the rearward left wing beam, and a right wing beam support structure
for
supporting an outer end of the forward right wing beam and the rearward right
wing beam.
The medial portion of the left wing beam support structure may include a left
front support
post extending downwardly to the ground, and rotatably moveable mounted to an
inner end
of the forward left wing beam. Similarly the medial portion of right wing beam
support
structure may include a right front support post extending downwardly to the
ground, and
rotatable moveable mounted to an inner end of the forward right wing beam.
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[0023] Various components of the aircraft shelter are mounted to the ground -
various types
of ground anchors and mounting will be understood by those skilled in the art
and are all
contemplated within the scope of the present invention.
[0024] In addition to embodiments of the aircraft shelter designed to protect
an aircraft
which is a fixed wing aircraft, other embodiments of the aircraft shelter
could be designed
for the protection of an an aircraft which was a helicopter - necessary
changes to the front
support beam and frame structure to accommodate the upper rotor shaft and lack
of wings
on such an aircraft will be understood to those skilled in the art and as
outlined the aircraft
shelter designed for the protection of either a fixed wing airplane or a
helicopter are all
contemplated within the scope of the present invention.
[0025] The aircraft shelter protects an aircraft from the elements, is easily
and cost
effectively manufactured and installed, and is easily opened and closed to
enable entry/exit
of the aircraft.
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE
DRAWINGS
[0026] To easily identify the discussion of any particular element or act, the
most
significant digit or digits in a reference number refer to the figure number
in which that
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element is first introduced.
[0027] FIG. 1 is a perspective front view of one embodiment of an aircraft
shelter for an
aircraft which is a low-wing airplane, and shows the aircraft shelter being in
an open
position.
[0028] FIG. 2 is a perspective front view of the aircraft shelter of Figure 1,
in a closed
position.
[0029] FIG. 3 is a top view of one embodiment of a structure for rotatably
mounting the
left front support beam and right front support beam to the rear section of
the aircraft
shelter. [0030] FIG. 4 is a front view of the components of Figure 3.
[0031] FIG. 5 is a detailed schematic view of the frame of one embodiment of
an
aircraft shelter in accordance with the invention, in closed position;
[0032] FIG. 6 is a front view of the frame of the aircraft shelter of Figure
5;
[0033] FIG. 7 is a detailed schematic view of an alternate embodiment of the
frame of
an aircraft shelter in accordance with the invention in open position;
[0034] FIG. 8 is a cutaway side view of one embodiment of a left wing beam
outer
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support structure in accordance with the present invention;
[0035] FIG. 9 is a detail view of one embodiment of a hem pocket attachment of
a
fabric cover to a longitudinal element.
[0036] FIG. 10 is a side view of one embodiment of a coupler for rigidly
coupling of the
left front support beam and the right front support beam.
[0037] FIG. 11 is a side view of one embodiment of a coupler for coupling each
of the
left front support beam and the right front support beam to the left front
support post
and right front supportpost, respectively.
[0038] FIG. 12 is a perspective front view of another embodiment of the
aircraft shelter,
where the aircraft is a high-wing, the aircraft shelter being in an open
position.
[0039] FIG. 13 is a perspective front view of the aircraft shelter of Figure
12, in a
closed position.
[0040] FIG. 14 is a perspective front view of another embodiment of an
aircraft shelter
in accordance with the present invention, wherein the aircraft is a
helicopter, the aircraft
shelter being shown in a closed position.
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DETAILED DESCRIPTION
[0041] Unless defined otherwise, all technical and scientific terms used
herein have the
same meaning as commonly understood by one of ordinary skill in the art to
which the
invention belongs. Although any methods and materials similar or equivalent to
those
described herein can be used in the practice or testing of the present
invention, the
preferred methods and materials are now described.
[0042] The present invention is an aircraft shelter for use in the storage and
shelter of an
aircraft. The aircraft shelter is easily assembled, with little requirements
in terms of
foundation or ground work on site, and allows for reasonably quick protection
to be applied
over an aircraft to protect it from the elements. The aircraft can be
reasonably quickly
placed into and out of the aircraft shelter, and the aircraft shelter provides
enhanced
protection for the aircraft and has structural integrity in inclement
conditions including
wind, rain and snow loads. The aircraft shelter can also optionally be locked
closed, to
allow for theft protection of the aircraft stored therein. The embodiments of
the invention
described herein are intended for protecting small aircraft such as, for
example, aircraft that
are considered "light aircraft" in the aviation industry. This being said,
however, while the
embodiments of the invention outlined herein demonstrate protection and
shelter of single
engine propeller driven aircraft, it will be evident to those skilled in the
art that the
embodiments of the invention are not limited thereto, but are also adaptable
for protecting
small twin engine propeller driven airplanes, small jet airplanes and glider
airplanes.
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[0043] Referring first to Figure 1 and Figure 2, there is shown an aircraft
shelter 100
which is intended for use in the shelter of an aircraft 102. Figure 1 shows
the aircraft
shelter 100 in an open position, and Figure 2 shows the aircraft shelter 100
in a closed
position, sheltering the aircraft 102. In this case the aircraft 102 which is
shown is a low-
wing airplane. The aircraft 102 as shown has a left wing 114 and a right wing
116. For
the purpose of describing the operation of the invention, the two sections of
the aircraft
102 which are described are the rear aircraft section and the front aircraft
section. The
rear aircraft section 106, as outlined in further detail herein, in the case
of a fixed wing
airplane, is the section of the airplane behind the trailing edge of the
wings, and the front
aircraft section 110 is the section of the airplane including the wings and
the fuselage
ahead of the wings to the front of the airplane - for example the cowling 118
and canopy
120 sections of the aircraft 102 as shown.
[0044] The aircraft shelter 100 includes a rear shelter section 104 for
covering a rear
aircraft section 106 in a protective manner, such that the front end of the
rear shelter section
104 is placed behind and in proximity to the trailing edge of the left wing
114 and the right
wing 116. A front shelter section 108 extends forward from the forward edge
112 of the
rear shelter section 104 and is moveable between a closed position for
covering at least a
substantial portion of the front aircraft section in a protective manner, and
an open position
for enabling entry and exit of the aircraft 102.
[0045] The rear shelter section 104 has a forward edge 112 which would be
positioned behind
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and in proximity to the trailing edges of the left wing 114 and the right wing
116 of the aircraft
102. The front shelter section 108 extends forward from the forward edge 112
of the rear
shelter section 104. The front shelter section 108 is moveable between an open
position
and a closed position - in the closed position, the front shelter section 108
will shelter a
substantial portion
of a front aircraft section 110 - for example the cowling 118 and the canopy
120 - and
when in the open position, the aircraft 102 can be moved into or out of the
aircraft shelter
100.
[0046] The rear shelter section 104 as shown includes a rear section support
frame 142
which is comprised of a plurality of rear shelter section members 124
positioned parallel to
each other and approximately perpendicular to axis 122. In this Figure 1
embodiment, the
number of arch- type rear shelter section members 124 is four. It will be
understood that
the number, size and shape of the rear shelter section members 124 could vary,
based for
example on the shape and size of the aircraft 102 that it was desired to
protect. As shown,
the rear shelter section members 124 are connected via longitudinal braces 132
and
diagonal braces 134 made of, for example, round, square or rectangular tubing
material, in
a conventional manner using standard tubing couplers or clamps. The number and
type of
longitudinal braces 132 and diagonal braces 134 used, as well as their shape,
construction
or other parameters could all be varied without departing from the scope and
intention
herein.
[0047] In many embodiments considered, each of the rear shelter section
members 124
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would be made up of a top segment 126, left wall segment 128 and right wall
segment 130
which were disconnectible from each other, using standard tubing couplers, to
facilitate
transport and handling (these sections of the members 124 are seen in Figure
5).
Preferably, the rear shelter section 104 is such that the defined rearward
shelter cavity
surrounds the rear aircraft section 106 in close proximity thereto to ensure a
small footprint
while enabling easy entry and exit of the rear aircraft section 106 by moving
the same
substantially along the axis 122 using, for example, a pushback tractor.
[0048] The rear shelter section members 124 support a rear section cover 136
made of, for
example, a flexible fabric material which is secured in a conventional manner
using straps,
buckles, and cinch straps fastened thereto or to conventional ground anchors.
Alternatively,
the rear shelter section 104 could also be constructed as a rigid shell
structure made of, for
example, a plurality of wall and roof sections. In the case of a rigid rear
section cover 136
defining the rearward shelter cavity, the rear section cover 136 might
comprise a series of
self-supporting cover sections, or might alternatively comprise rigid cover
sections on a
rear section support frame. Either flexible or rigid construction of the rear
section cover
136 is contemplated within the scope hereof.
[0049] Each of the rear shelter section members 124 is secured to a ground
anchor,
such as, for example, a conventional auger/helix ground anchor, using, for
example, a
standard clevis and clevis pin coupler. Many methods and apparatus for the
removable
or rapid ground anchoring of components will be understood to those skilled in
the art of
portable structure design, and all methods of ground attachment of these and
other
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components of the aircraft shelter 100 will be understood to be within the
scope of the
present invention.
[0050] A front shelter section 108 comprises a left front support beam 138 and
a right front
support beam 140, which are moveably mounted to the forward edge 112 of the
rear shelter
section 104 in proximity to the top segment 126 thereof such that when the
aircraft shelter
100 is in the closed position the left front support beam 138 and the right
front support
beam 140 are disposed above the front aircraft section 110 and extend forward
from the
forward edge 112 and above the aircraft 102. Preferably, each of the left
front support
beam 138 and the right front support beam 140 are mounted rotatably to the
forward edge
112 of the rear shelter section 104 such that they can each be rotatably moved
in either or
both of a substantially vertical and a substantially horizontal direction.
Referring to Figure
3 there is shown in detail one mounting of the left front support beam 138 and
the right
front support beam 140 to the rear shelter section 104 - left hinge 302 and
right hinge 304
enable rotational movement about the left vertical axis 306 and right vertical
axis 308,
respectively, and are mounted in close proximity to each other to the forward
edge 112 of
the rear shelter section 104, typically to the forward most of the rear
shelter section
members 124, near its apex. A mounting plate 310 is shown which is mounted to
the
forwardmost of the rear shelter section members 124 using conventional means.
The left
hinge 302 is attached to the left front support beam 138 via a U-shaped left
coupling
member 312 and a left clevis pin 316 and a related split or cotter pin,
enabling rotational
movement around horizontal axis 320. Similarly, the right hinge 304 is
attached to the
right front support beam 140 via a U-shaped right coupling member 314 and a
right clevis
pin 318 and a related split or cotter pin, enabling horizontal movement of the
right front support
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beam 140 around horizontal axis 320. The attachment of the left front support
beam 138 and the
right front support beam 140 to the rear shelter section 104, allowing dual
axis rotational
movement, could be done with other hardware and in different ways and any such
attachment
method accomplishing the same goal is contemplated within the scope hereof.
Alternatively,
the left front support beam 138 and the right front support beam 140 might be
removably
mounted to the apex of the forward edge 112 of the rear shelter section 104
using, for example,
screw bolts or the like. Figure 4 shows a front view of the component view of
Figure 3.
[0051] The rotational movement of each of the left front support beam 138 and
the right
front support beam 140 around the left vertical axis 306, the right vertical
axis 308 and the
horizontal axis 320, and the rotational movement between each of the left
front support
beam 138 and the right front support beam 140 and the left front support post
144 and the
right front support post 146, respectively, substantially facilitates the
movement of the same
upward and rearward over the left wing 114 and the right wing 116 of the
aircraft 102, to
open the front shelter section 108 and vice versa for moving same to the
closed position.
Preferably, in the closed position, the
left front support beam 138 and the right front support beam 140 are disposed
in close
proximity to each other and substantially rigidly coupled to each other via a
support beam
coupler 152. Figure 10 shows one example of a support beam coupler 152, which
is a clevis
and pin arrangement, to increase the rigidity and strength of the combined
left front support
beam 138 and right front support beam 140.
[0052] The left front support beam 138 is preferably rotatably and moveably
attached at its
distal end from the mounting plate 310 to a left front support post 144, and
the right front
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support beam 140 is similarly attached at its distal end from the mounting
plate 310 to a
right front support post 146. Each of the left front support post 144 and the
right front
support post 146 extend downwardly to the ground for supporting the same in a
conventional manner, using for example, a clevis and pin arrangement as shown.
Each of
the left front support post 144 and the right front support post 146 is
securable to a ground
anchor which could again be of many different types. Optionally, the aircraft
shelter 100
might be lockable in the closed position by providing locking hardware to
fixedly attach left
front support beam 138 and right front support beam 140 to each other.
[0053] The left front support beam 138 and the right front support beam 140
together with
the left front support post 144 and the right front support post 146 support
respectively a
left front section cover 148 and a right front section cover 150 made of a
flexible fabric
material for covering at least a substantial portion of the front aircraft
section 110, with the
left front section cover 148 and the right front section cover 150 extending
forward from
the forward edge 112 of the rear shelter section 104.
[0054] As shown in Figure 2, in the closed position the left front support
beam 138 and the
right front support beam 140 are placed above the front aircraft section 110,
with the left front
support post 144 being oriented downward and to the left-hand side of the
aircraft 102 and the
right front support post 146 being oriented downward and to the right-hand
side of the
aircraft 102. Preferably an upper edge portion of the left front section cover
148 and the
right front section cover 150 are mounted to the left front support beam 138
and the right
front support beam 140, respectively, and a front edge portion of the left
front section
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cover 148 and the right front section cover 150 are mounted to the left front
support post
144 and the right front support post 146, respectively, in conventional manner
using, for
example, hem pockets disposed in the left front section cover 148 and the
right front
section cover 150 accommodating the respective portions of the left front
support beam
138, left front support post 144, right front support beam 140 and right front
support post
146 therein. The left front section cover 148 and the right front section
cover 150 are
secured in a conventional manner using straps, buckles, and cinch straps 112
fastened to
the left front support post 144 and right front support post 146 and/or to
conventional
ground anchors. Other front support beam configurations could also be used
without
departing from the scope and intention hereof.
[0055] Figure 5 demonstrates one embodiment of the structural frame of an
aircraft shelter
100 in accordance with the invention. There is shown the rear shelter section
104 and the
rear shelter section members 124. The front shelter section 108, forward of
the forward
edge 112 of the rear shelter section 104 is also shown. The front shelter
section 108
includes a left wing shelter section 154 and a right wing shelter section 156,
as shown in
Figure 1 and 2, capable of protecting the outboard portions of the left wing
and right wing
of the aircraft 102, where the aircraft 102 is a fixed wing aircraft. As
shown, the left wing
shelter section 154 includes a rearward left wing beam 502 laterally extending
outward
from the forward most of the rear shelter section members 124, at the forward
edge 112 of
the rear shelter section 104. The rearward left wing beam 502 extends to
beyond the
wingtip of the left wing 114 of the aircraft 102. Similarly the right wing
shelter section 156
includes a rearward right wing beam 504 extending laterally outwards from the
right side
of the rear shelter section 104, from the forward most of the rear shelter
section members
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124, at the forward edge 112 of the rear shelter section 104. The rearward
right wing beam
504 extends to beyond the wingtip of the right wing 116 of the aircraft 102.
The rear shelter
section 104 and the rearward right wing beam 504 are mounted to the forward
most of the
rear shelter section members 124 such that they are disposed above the ground
approximately higher or equal to the height of the trailing edge of the left
wing 114 and the
right wing 116 of the aircraft 102.
[0056] The left wing shelter section 154 includes a forward left wing beam 506
located in
front of a leading edge of the left wing 114 of the aircraft 102, such that
the forward left
wing beam 506 is disposed above the left wing 114 and in proximity thereto.
Similarly, the
right wing shelter section 156 al so includes a forward right wing beam 508
located in front
of a leading edge of the right wing 116 of the aircraft 102, above the right
wing 116 and in
proximity thereto.
[0057] A left cantilever beam 510 is mounted to the rear shelter section 104
and extends
forward therefrom to support an inner end of the forward left wing beam 506.
Similarly, a
right cantilever beam 512 is mounted to the rear shelter section 104 and
extends forward
therefrom to support an inner end of the forward right wing beam 508. At the
distal ends of
the rearward left wing beam 502 and the forward left wing beam 506, a left
outer wing
beam support 514 holds and supports those beams in relation to each other and
strengthens
the left wing shelter section 154. Similarly, at the distal ends of the
rearward right wing
beam 504 and the forward right wing beam 508, a right outer wing beam support
516 holds
and supports those beams in relation to each other and strengthens the right
wing shelter
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Docket No: 663-003
section 156. A plurality of wing beam support structures 518 extend downwards
from the
rearward left wing beam 502, the rear aircraft section 106, the forward left
wing beam 506
and the forward right wing beam 508 to support the left wing shelter section
154 and the
right wing shelter section 156 above the ground. The wing beam support
structures 518 are
preferably secured to ground anchors. As in the case of other points of the
aircraft shelter
100 anchored to the ground, ground anchors of many types could be used.
[0058] The framing structure shown in Figure 5 includes a forward cover
support panel,
mounted between the left cantilever beam 510 and the right cantilever beam 512
for the
purpose of providing support to the left front section cover 148 and the right
front section
cover 150 when closed over the aircraft 102. This panel could further
strengthen the front
shelter section 108 and provide additional support for the left front section
cover 148 and the
right front section cover 150, by supporting that fabric on top of the forward
section support
member 524. The forward cover support panel includes at least one forward
section support
member 524, and two frame member 528 are shown. This forward cover support
panel is
intended to reduce the distance that the Heft front section cover 148 and
right front section cover
150 are cantilevered over the front aircraft section 110, by shortening the
left front support beam
138 and the right front support beam 140 and moving their point of attachment
forward from the
forward edge 112 of the rear shelter section 104 to the forward panel hinge
point 530. The
forward cover support panel could be constructed or integrated into the front
shelter section
108 in many different specific formats, all of which are intended within the
scope of the
present invention insofar as they accomplish the objective of providing
support for the left
front section cover 148 and the right front section cover 150 forward of the
forward edge
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112 of the rear shelter section 104, and/or decreasing the distance that the
cantilever of the
front shelter section 108 extends over the aircraft 102.
[0059] Also shown are a plurality of forward partial support member 526
elements,
extending outwardly from the left front support beam 138 and the right front
support beam
140 to provide further support to the left front section cover 148 and the
right front section
cover 150, to keep them off or supported over the upper area of the front
aircraft section
110. In this case six forward partial support member 526 elements are shown.
[0060] Also shown is a left wing beam support post 520 supporting an inner end
portion of
the forward left wing beam 506, extending downwardly therefrom to the ground
and
anchored to the ground, and a right wing beam support post 522 supporting an
inner end
portion of the forward right wing beam 508 extending downwardly to the ground
and
anchored to the ground. Preferably the left wing beam support post 520 and the
right
wing beam support post 522 are rotatably mounted to their respective forward
wing
beams, allowing rotation of same in an upward direction to enable entry and
exit of the
left wing 114 and the right wing 116 of the aircraft 102 into and from the
left wing
shelter section 154 and the right wing shelter section 156 respectively.
Optionally the
left wing beam support post 520 and the right wing beamsupport post 522 are
removably mounted using, for example, screw bolts or pins.
[0061] The left cantilever beam 510 and the right cantilever beam 512 could be
adapted to withstand weather and wind and snow loads acting on the respective
left
wing shelter section 154 and the right wing shelter section 156, allowing for
omission
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of the left wing beam support post 520 and the right wing beam support post
522.
[0062] Figure 6 shows a front view of the frame structure of Figure 5, in a
closed
position.
[0063] While it is conceived that many embodiments of the aircraft shelter 100
would
include the forward cover support panel and the plurality of forward partial
support
member 526 elements detailed in Figure 5 and Figure 6, Figure 7 demonstrates
another
embodiment of the frame structure of the aircraft shelter 100 of the present
invention,
without the forward cover support panel. This frame is shown in open position.
[0064] Shown next in the embodiment of Figure 1 et al. are a left wing shelter
section
154 and a right wing shelter section 156 each of which extends substantially
laterally
from near the forward edge 112 of the rear shelter section 104, and the front
shelter
section 108, for covering the left wing 114 and right wing 116 of the aircraft
102,
respectively. The left wing shelter section 154 comprises a flexible fabric
left wing
cover 158 to cover the left wing 114 of the aircraft 102 and the right wing
shelter
section 156 comprises a flexible fabric right wing cover 160 to cover the
right wing
116 of the aircraft 102. Each of the left wing cover 158 and the right wing
cover 160 is
preferably supported by a frame structure such that the fabric wing covers do
not touch the
wings of the aircraft 102.
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[0065] Figure 8 shows a cutaway side view of a left wing shelter section 154
in accordance
with an embodiment of the invention, demonstrating the positioning and
interaction of
various components of the left wing shelter section 154 with the left wing 114
of the
aircraft 102 in position therein. Preferably the wing beam support structures
518, left outer
wing beam support 514 and the left wing beam support post 520 are
telescopically
adjustable in a substantially vertical direction as directed by the block
arrows in Figure 8,
thus enabling the left wing shelter section 154 and the right wing shelter
section 156 to be
adjusted for different aircraft 102 such as low wing or high wing airplanes.
Optionally, the
rearward left wing beam 502 and forward left wing beam 506 could also be
telescopically
adjustable to accommodate aircraft 102 having different wing spans.
Alternatively, the left
wing shelter section 154 could comprise only the rearward left wing beam 502
with the left
wing cover 158 - secured to ground anchors in front of the left wing 114 with
the aircraft
102 in place therein, the left wing cover 158 being in contact with a top
portion and leading
edge of the wing in such embodiments. The embodiment of Figure 8 shows a
cutaway
view of an outboard left wing shelter section 154. The right wing shelter
section on the
other side of the aircraft could be manufactured in a reflective fashion such
that the
configuration of that section of the aircraft shelter was reflective in form
and function
except that the right wing shelter section extends outwardly approximately
perpendicular to
the right of the aircraft fuselage, versus to the left.
[0066] Preferably, the covers for the rear shelter section 104, the front
shelter section 108,
the left wing cover 158 and right wing cover 160 are provided as separate
covers secured to
the respective frame structures via hem pockets and/or cinch straps for
interacting with
grommets disposed in the covers for tightening the same in a manner known to
one skilled
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in the art. Figure 9 is a detail view of a hem pocket configuration of a
flexible fabric cover,
for example the left wing cover 158 or the right wing cover 160 - hem pocket
162 is
disposed along the lower edge of a cover, accommodating longitudinal member
164 therein.
Cutaway 166 are disposed at predetermined locations allowing straps or cinch
straps 202 to
interact with the longitudinal member 164 for securing the various flexible
fabric covers
such as the left wing cover 158 and right wing cover 160 to ground anchors or
support
members.
[0067] The front and rear edges of the left wing cover 158 and right wing
cover 160 each
comprise a hem pocket 162 accommodating a longitudinal member 164 therein, as
shown
in Figure 9. Adjustable cinch straps 202 interacting with the longitudinal
member 164 are
attached to maintain tension on the left wing cover 158 and right wing cover
160.
Optionally each of the left wing cover 158 and right wing cover 160 further
comprise a
hem pocket for accommodating the forward left wing beam 506 and forward right
wing
beam 508 respectively, thus allowing a front portion of each of the left wing
cover 158 and
right wing cover 160 to be released and folded on top of the left wing cover
158 and right
wing cover 160 , allowing entry and exit of the left wing 114 and right wing
116 into and
from the respective left wing shelter section 154 and right wing shelter
section 156 while
the remaining portion of each flexible wing cover remains secured in place.
Alternatively
the cinch straps 202 are secured to respective ground anchors.
[0068] Preferably, adjacent covers have sufficient overlap to ensure
protection of the
airplane and are, for example, secured to each other using snap fasteners or
hook and loop
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fasteners. The flexible fabric material is, preferably, chosen from a large
variety of
commercially available materials known in the art as 'Marine Canvas' materials
such as, for
example, acrylics, PVC coated polyester vinyls, silicon treated substrates and
coated meshes
for outdoor use. Most marine canvas materials offer UV and UVB resistance,
substantial
strength, and, to some extent, water resistance or waterproofness.
[0069] The left wing cover 158 and right wing cover 160 might optionally
include cutouts
to accommodate, for example, the engine cowling of a twin engine aircraft 102.
Alternatively, the high wing configuration of the design will accommodate twin
engine
aircraft.
[0070] Preferably the rear section cover 136, the left front section cover 148
and right
front section cover 150, and the left wing cover 158 and right wing cover 160
are provided
as separate covers secured to the respective sections of the frame of the
aircraft shelter 100
via hem pockets and/or cinch straps 202 for interacting with grommets disposed
in the
covers for tightening same in a manner known to those skilled in the art.
Preferably
adjacent covers have sufficient overlap to ensure protection of the aircraft
102 and are, for
example, secured to each other using snap fasters, hook and loop fasteners or
the like.
[0071] To open the aircraft shelter 100 in the embodiments shown, the cinch
straps 202
securing the left front section cover 148, right front section cover 150 and
the left wing cover
158 and right wing cover 160 are released. The front sections of each of the
left wing cover
158 and right wing cover 160 are then folded up on top of the respective left
wing cover 158
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and right wing cover 160. The left wing beam support post 520 and the right
wing beam
support post 522 are then rotated upwards and secured in the upper position.
The support
beam coupler 152 is then opened to release the left front support beam 138 and
the right front
support beam 140, while the left front support post 144 and the right front
support post 146 are
released from their ground anchors. Finally the left front support beam 138
and the right front
support beam 140, and the associated left front section cover 148 and right
front section cover
150 and left front support beam 138 and right front support beam 140 are moved
upwardly and
rearwardly such that the left front support post 144 and right front support
post 146 are moved
over and placed to the rear of the respective left wing shelter section 154
and right wing
shelter section 156. To close the aircraft shelter 100, the inverse of these
steps is performed
in reverse order to close, fasten and cinch the covers into place.
[0072] Figure 10 and Figure 11 provide detail views of further specific
components of the
aircraft shelter 100 of Figure 1.
[0073] While the embodiment of Figure 1 and Figure 2 demonstrates an aircraft
shelter 100
for sheltering a low-wing aircraft 102, Figure 12 and Figure 13 show an
alternate
embodiment of an aircraft shelter 100 which is designed for the sheltering of
a high-winged
airplane as the aircraft 102, Figure 12 showing that embodiment in an open
position and
Figure 13 in a closed position.
[0074] Figure 14 shows another embodiment of the aircraft shelter 100 of the
present
invention, in a closed position, wherein the aircraft 102 is a helicopter.
Here, the forward
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edge 112 of the rear shelter section 104, covering the rear aircraft section
106 such as, for
example, the tail and stabilizer (not shown) - is placed behind rotor shaft
1402 of the
aircraft 102 and in proximity thereto. The front shelter section 108 comprises
left front
support beam 138 and right front support beam 140 movable mounted to the
forward edge
112 of the rear shelter section 104 as described above. Each of the left front
support beam
138 and the right front support beam 140 is preferably rotatable moveable -
mounted to a
respective left front support post 144 and right front support post 146
extending
downwardly to ground for supporting the same as described hereinabove for the
aircraft
shelter 100.
[0075] The left front support beam 138 and right front support beam 140 are
placed above
the cabin of the aircraft 102 with the left front support post 144 being
oriented downward
and to the left-hand side of the aircraft 102 and the right front support post
146 being
oriented downward and to the right-hand side of the aircraft 102. Each of the
left front
support beam 138 and right front support beam 140 shown in this embodiment
have a
curved section adapted for surrounding a portion of the rotor shaft 1402 of
the aircraft 102
in the closed position. Alternatively, the curved sections are omitted and the
left front
support beam 138 and right front support beam 140 are mounted to the forward
edge 112 of
the rear shelter section 104 spaced apart a distance greater equal to the
diameter of the rotor
shaft of the aircraft 102 and rigidly and removably connected to each other
via a coupling
element disposed therebetween.
[0076] It will be recognized that the specific materials used in constructing
the various
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components of the system described herein, are not considered to be limiting
to the scope of
the invention. Those of skill in the art will readily recognize and be able to
select materials
and components that will accomplish the objectives of the invention without
requiring any
inventive skill.
[0077] It should also be apparent to those skilled in the art that many more
modifications
besides those already described are possible without departing from the
inventive concepts
herein. The inventive subject matter, therefore, is not to be restricted
except in the scope of
the appended claims. Moreover, in interpreting both the specification and the
claims, all
terms should be interpreted in the broadest possible manner consistent with
the context. In
particular, the terms "comprises" and "comprising" should be interpreted as
referring to
elements, components, or steps in a non-exclusive manner, indicating that the
referenced
elements, components, or steps may be present, or utilized, or combined with
other
elements, components, or steps that are not expressly referenced.
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