Note: Descriptions are shown in the official language in which they were submitted.
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Method and apparatus for spacecraft propulsion with a field shield
protection
Inventor: Stoyan Sargoytchev,
1 Massey Square, apt. 1212
Toronto, Ontario
Canada, M4C 5L4
BACKGROUND OF THE INVENTION
The present invention relates to a method and apparatus for creating a
propulsion effect and
a field shield protection in order to be used by a spacecraft preferably in a
deep space. The goal is
to create a force field and a protective field shield without throwing or
emission of mass particles
that means using only electric, magnetic and electro-magnetic fields in a
proper combination. In
the prior art literature such kind of propulsion system is referred as
massless space drive or
propulsion.
The main disadvantage of the massless propulsion methods described in the
prior art is that
they don't rely on understandable physical mechanism. They are usually a
product of
experimentally discovered anomalous behavior without understandable physics.
In most cases the
inventors or authors suggest explanations contradicting to the known laws of
physics or in the best
way they propose empirical models without touching the contradictions to known
physical laws. In
both cases the phenomenon could not be scaled and optimized for practical
application, due to lack
of understanding the physical mechanism.
One of the massless propulsion methods, known as Biefield-Brown effect is
described
initially in US patents 3,018,394 (1962) and 3,022,430 (1962). In the prior
art literature this effect
is known also as electrogravity. The effect is a week propulsion force in the
direction of the
positive electrode of a capacitor-like actuator charged with a DC high
voltage. The observable
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force field is possible only at high voltages above tens of thousand. For
practical applications
voltages in order of hundred thousands and even millions are required, while a
parasite arc
discharge must be avoided. This puts severe constraints for designing of a
spacecraft that must
operate at different atmospheric pressure and in deep space. It is still
disputable that the effect
might be a result of ion wind, since the polarity of the electrodes is
constant.
Woodward et al. in US patent 6,098,924 describe an accelerator based on a
piezoelectric
devices attached to resonant mechanical structures. The method lacks a
physical explanation and
only a small-scale effect is reported.
Podkletnov and Modanese [arXiv:physics/0108005v2, 2001] reported small effect
from
impulse gravity generator based on a charged Yba CuO superconductor. The major
disadvantages
are cryogenically cooled environment (about -196 C), a high vacuum and very
small reported
efficiency 1-2%. NASA spent $600,000 for attempts to replicate this experiment
without success.
The final attempt to replicate the experiment by G. Hathaway with a 50 times
higher accuracy and
consulted by Podkletnov through the experiment shows that the effect is
illusive [G. Hathaway,
Physica C, 385, 2003, p.488-500].
J. Reece Roth et al. in US patent 6,200,539B 1(2001) titled "Paraelectric Gas
Flow
Accelerator" describes an accelerator consisting of two sets of parallel metal
stripes from both
sides of an insulating plate properly displaced. The stripes of each set are
connected together.
When a high AC voltage is applied in the kilohertz frequency range a specific
glow discharge
appears between the electrodes and one observes a weak acceleration effect in
respect to the
surrounding gas atmosphere. Since the glowing plasma is obtained at normal
atmospheric pressure,
the method is called One Atmospheric Pressure Glow Discharge (OAPGD). The
activated plasma
emits a broad band RF spectrum in the range of 1 to 250 Mhz. According to
Roth, the observed
small acceleration effect is a result of Lorentzian collisions of ions and
electrons with the neutral
molecules, atoms and radicals. This explanation is not satisfactory from a
physical point of view
because the plasma is excited at each half cycle of the AC filed, so the
electrodes polarity changes
alternatively, while the acceleration is unidirectional. For this reason many
researchers who
investigate this type of accelerators express the idea that the effect is
unknown. The effect exhibits
also a small turbulence reduction, for which there is not any physical
explanation in the prior art.
Roth and other researchers consider that the thrust force is a kind of
reaction of the
surrounding. In such aspect they do not envision a possible operation in a
deep space and does not
offer provisions for such applications. Since the physics of the observed
phenomenon is not
understood, they could not provide effective recommendations for design and
optimization of the
efficiency of their accelerators. There are two major disadvantages if trying
to use the Roth's
OAPGD method in a deep space. The first one is that with the proposed method
of plasma
activation the propulsion effect is very weak. The second one is that a sniall
fraction of the power
supplied to the accelerator, which behaves as a capacitor load, contributes to
the force filed, so the
power efficiency is quite low. The suggested by Roth passive network adapter
only slightly
reduces the useless reactive power. Such adaptor also could not be used at
different environment
pressure, which means working at different heights above the ground.
Another researcher and inventor S. Roy suggests a Wingless Electromagnetic Air
Vehicle
(WEAV) based on his research on the Dielectric Barrier Discharge. He does not
goes further that J.
Roth about the physics of the phenomenon, proposing only empirical models for
his particular
model and does not propose means for use in deep space including a protective
field shield against
micrometerorites.
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In the recent 15 years the research in a field known as Electrohydrodynamics
is intensified
in USA, Europe and Russia. Despite of this a possible existance of a gravito-
inertial effect has not
been envisioned in the prior art.
For a spacecraft moving with very high velocity it becomes very necessary to
have a
protective filed shield against micrometerorites in a deep space and dust
particles in atmosphere.
There is not provision for such kind of protection in the prior art.
SUMMARY OF THE INVENTION
It is an object of the invention to propose a method and apparatus for
propulsion of
spacecraft with a field shield protection, in which the propulsion is a result
of unidirectional
change of the gravito-inertial mass of the spacecraft, while the spacecraft is
surrounded by a field
shield that protect it from micrometeorites.
It is another object of the invention to provide design considerations for the
shape of the
spacecraft with positions of the functional members of the propulsion system.
It is another object of the invention to improve the prior art plasma thrust
accelerators in
order to be used in a spacecraft operating in a planetary atmosphere and in
deep space.
It is another object of the present invention to increase the efficiency of
the prior art plasma
thrust accelerators by applying simultaneously AC and DC high voltage fields.
It is another object of the present invention to propose a circuit that
prevents returning the
reactive power from the capacitive type of plasma thrust actuator back to the
AC high voltage
power supply in order to increase the power efficiency of the force field.
The physics of the propulsion method and the field shield is provided by the
Basic
Structures of Matter - Supergravitation Unified theory (BSM-SG), published as
a monograph by
the author of this invention. The proposed propulsion method is based on the
effect called
Stimulated Anomalous Reaction to the Gravity (SARG). A small scale of SARG
effect is
experimentally demonstrated in a laboratory. The protective field shield, the
physics of which is
also explainable by BSM-SG theory, relies on combination of EM field and
superluminal waves,
known as X-waves or Evanescent mode, emitted by means with properly selected
parameters.
The invention, the theoretical bases and the experiments demonstrating its
validity are
described further below with the reference to the accompanied drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 illustrate the helical trace and the magnetic field of an electron
bound to a moving single
ionized atom, forming an ion-electron pair
Fig. 2 shows a simple thrust actuator for demonstration of the SARG effect.
Fig. 3 shows electrical means for activating the simple plasma thrust actuator
demonstrated SARG
effect
Fig. 4 shows the waveform measured by antenna at 1.5 m distance from the
plasma actuator
Fig. 5 shows a dual-section plasma thrust actuator activated by AC High
Voltage circuitry with
increased power efficiency
Fig. 6 shows a basic electrode configuration for creation of protective field
shield
Fig. 7 shows the timing diagram of emitted signals for creation of a
protective field shield
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Fig. 8 shows the main functional blocks of a disc-shape spacecraft for a close
range interplanetary
flight
Fig. 9.a, b shows an overall shape of a spaceship for a long range travel with
allocated positions of
propulsion devices based on the SARG effect
Fig. 10. shows one preferable embodiment of a high voltage AC+DC circuits for
the disc-shaped
spacecraft
DETAILED DESCRIPTION
The propulsion method is based on a gravito-inertial phenomenon predicted by
the Basic
Structures of Matter - Supergavitation Unified Theory (BSM-SG) [1,2,3,4,5],
developed and
published as a monograph by the author of this invention. According to this
phenomenon, the
gravito-inertial mass of an object could be changed unidirectionally by proper
modulation the
parameters of the physical vacuum. The experimental demonstration of this
phenomenon is called
a Stimulated Anomalous Reaction to Gravity (SARG) effect [11]. The application
of the SARG
effect in a spacecraft suggests the use of a neutral plasma, partially or
fully surrounding the
spacecraft and activated by electromagnetic and electrical fields. The result
is a unique force field
distinguished from the reactive propulsion by a lack of throwing mass, a
reduced or eliminated
reaction for the acceleration and reduced turbulence in atmosphere.
The suggested propulsion method has not been envisioned by the Modern Physics,
since
the concept of the physical vacuum adopted at the beginning of 20 century does
not correspond to
reality. After Albert Einstein developed his famous theory in General
Relativity, he realized that
the Ether is nessesary. In his monograph Sidelights on Relativity (1921) [1]
Einstein says:
"Recapitulating, we may say that according to the general theory of relativity
space is endowed
with physical qualities; in this sense, therefore, there exists an ether.
According to the general
theory of relativity space without ether is unthinkable; for in such space
there not only would be no
propagation of light, but also no possibility of existance for standards of
space and tiem.
(measured-rods and clocks), nor therefore any space intervals in the physical
sense".
The only argument of Einstein against the material Ether in 1921 is that the
physicists
failed to build a working model based on Maxwell assumption. Now it is known
that the
Michelson-Morley experiment is inconclusive due to a methodological error,
namely: The Effect
of Doppler shift is compensated by the effect of relativistic clock rate
change. Both effects affect
the wavelength so the expected interferometric fringe shift is nullified. (The
effect of clock rate
change has been unknown at the time when Michelson-Morley experiment was
done). Michelson
himself highly doughted the result and suggested experiments with counter
propagated light
packets (Fig. 4 of Michelson-Morley paper [2], having a right intuition that
the result will be quite
different. Such experiment was not funded during his life. Original
experiments based on
interrupted counter propagated light packets were firstly realized by Prof.
Stefan Marinov. In the
period 1972-1982 he made 3 different laboratory experiments [3,4,5]. He not
only successfully
detected our absolute motion in the Ether medium, but derived the magnitude
and the direction of
the velocity vector:
magnitude: 360 +/- 40 km/s
direction: l= 313 y= 39 - in galactic coordinates
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Number of other modern ether-drift experiments confirm our absolute motion
through
some existing space medium - Ether.
The BSM-SG theory [6,7,8,9,10] suggest that at the bottom level of all matter
are two
indestructible fundamental particles (FP) of different intrinsic matter with
parameters associated to
the Planck's scale of the frequency and distance. In a pure empty space these
two particles interact
by Supergravitational (SG) forces, which are distinguished by the Newtonian
gravitation that they
are proportional to the cube of the distance.
FsG = GO m0~m02 (1)
where: moi and m02 - SG masses; r -distance; Go - SG constant that is
different for FPs of a same
and a different intrinsic matter
Under SG law and pure geometrical restrictions the two fundamental particles
congregate
in geometrical formations following a unique crystallization process (see BSM-
SG theory Chapters
2 and 12). This process leads to crystallization of two prism-like sub-
elementary particles with
internal twisted structure, so they are called twisted prisms. They build
both, the underlying
structure of the space (physical vacuum) and the material structure of the
elementary particles.
The underlying structure of the space is called a Cosmic Lattice (CL) and it
provides the
known physical and quantum mechanical properties of the physical vacuum. The
individual CL
node is formed by 4 twisted prisms of the same type hold together by (SG)
forces. If considering
an isolated CL node the 4 prisms are at mutual angles of - 109.50
corresponding to the axes in a
tetrahedron. The CL space is formed from the two alternative types CL nodes
arranged like the
atoms in a diamond. The SG forces between the opposite CL nodes also may
change the sign from
their mutual distance, since they depend on the common super-high proper
frequency. This gives
the possibility for spatial gaps between the CL nodes and consequently a
vibrational freedom. The
same sub-elementary particles (twisted prisms) are embedded also into the
material structures of
the elementary particles. In the CL space environment (physical vacuum) the SG
forces are strongf
at atomic scale distance, so they hold the protons and neutrons in the atomic
nuclei. They
correspond to the well known strong nuclear forces. One type of Wan Der Wall
forces between the
closely spaced atoms and molecules are also a signature of the SG forces.
Another signature is the
observed Casimir force between two closely spaced polished surfaces. SG forces
are observed also
in the nanotechnology. The Suggested physical model works quite well in all
fields of Physics:
Particle physics, Quantum Mechanics, Newtonian gravity and inertia, Special
and General
Relativity, atoms, molecules, and Cosmology. The existence of the physical
substance of the
space, denoted in BSM-SG theory as a CL space, is confirmed by the modern
light velocity
experiments performed in a laboratory and detecting our absolute motion
through the space with a
velocity vector of magnitude about 360 km/s [3,4,5].
The flexible CL node has two axes of symmetry: one set of four axes denoted as
abcd
aligned with the axial axes of the twisted prisms and thee orthogonal axes
denoted as xyz axes.
Both sets of axes define a unilateral tetrahedron. Each CL node from one type
subelementary
particles has four neighboring CL nodes from the other type subelementary
particles. The two sets
of axes of the neighboring CL nodes are aligned, while their oscillations only
slightly affect their
mutual distances and alignment. Investigating the dynamics of the CL node
under SG law and
more specifically the return forces along the two sets of axes, provided a new
understanding of the
relation between the electric, magnetic and EM fields from one side and the
Newtonian gravity
from the other. The oscillations along xyz axes involve SG forces which are
thousands times
CA 02638667 2008-08-26
weaker than oscillations along the abcd axes. The EM field and light
propagation involves mainly
oscillations in a narrow angle along xyz axes, while the Newtonian gravity
appears as SG gravity
propagated along the abcd axes.
The BSM-SG unveils the material structure of the stable elementary particles,
such as
proton, neutron, electron and positron built by the same subelelemntary
particles (twisted prisms)
but arranged in helical structures with hierarchical order. The internal space
volume of the helical
structures contain internal space occupied by a lattice build by the same
subelementary particles
(twisted prisms but much denser than the CL structure, so the latter exercises
a pressure on that
volume. Using the unveiled structure of the electron and its quantum
interaction with the CL space
(Physics Essays, 16, No2, 180-195, (2003)), the suggested model permitted to
express important
physical constants by the CL space parameters (BSM-SG, Chapter 3):
- Static CL pressure, PS - (a pressure exercised on impenetrative volume of
the elementary
particle structure, defining the Newtonian mass of the elementary pareticle).
- PS=mecz/V =1.3736x1026(NIm2) (2)
where: Ps - is the static CL pressure, me - mass of electron, c - speed of
light, Ve -
inpenetralble volume of the electron structure
- Dynamic CL pressure, PD - (related to the Zero Point Energy of Dynamic type
and
responsible for the electrical and magnetic fields and the quantum behavior of
the
elementary particles):
Po = hv,/(cse) = 2025.s(N/(m2Hz)) (3)
where: h - Planck constant, vC - Compton frequency, Se - impenetrable surface
of the electron
structure
- Partial CL pressure, Pp - related to the confined motion of the electron
with one of its
quantum velocities "U , in which the signature of the fundamental Fine
Structure Constant
a plays a role. This influences the motion of the atoms, molecules and solids.
Pp = Psavlc (4)
For v= ac one obtains: P,, /PS = a2 (1- a) Z
The Dynamic CL pressure is related to the Zero Point Energy, envisioned by
Quantum
Mechanics. The Static CL pressure is related to a hidden Zero Point Energy,
envisioned by the
BSM- SG theory. For this pressure the Einstein Equation E = mcz is valid.
Using the Static CL
pressure the mass equation (5) of a stable elementary particles is derived
(BSM-SG, Chapter 3).
4hv~.4(1-aZ) (5)
m ~azcs VIr where: Vp - is the impenetrable volume of the elementary particle,
h - is the Planck constant
The Complex CL node dynamics is characterized by two identifiable cycles - one
with a
proper resonance frequency VR = 1.093 x 10Z9 Hz (defining light velocity as
one cycle per one CL
node distance) and the Compton's time with a frequency v(. = 1.236 x 1020 Hz,
defining the
permittivity and permeability of the physical vacuum (BSM-SG, Chapter 2). The
Compton cycle
involves a lot of number of whole resonance cycles.
Since the neighboring nodes are interconnected by SG forces, the following
unveiled
features of the CL node are quite important for understanding the properties
of the physical
vacuum:
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CA 02638667 2008-08-26
= SG forces are based on frequency higher than the proper resonance frequency
of the CL
node, while their propagation hrough CL structure as a Newtonian gravity
depends on the
mutual phases of the oscillating CL nodes.
= The mutual interaction between the oscillating CL nodes causes a
selfsynchronization at
the Compton's frequency of the CL node.
= The effect of selfsynchronization appears as permanently existed and
recombining
zeropoint waves. They are responsible for the constant value of eo and o
defining the
constant light velocity according to the expression
c = (EoNro )1,2 (6)
In Chapter 10 of BSM-SG, it was shown that the inertia of a solid object is
related to the
integral inertial momentum of displaced and folded CL nodes, which is
expressed by the force
moment vector, EIFM. This vector, defining the inertial properties, is able to
describe any kind of
motion: uniform, rotational or accelerated. For a single particle with mass m
it is:
E,rM = camv (7)
where: c - speed of light, a - fine structure constant, m - particle mass, v-
velocity.
Eq. (6) shows that the EIFM vector will get a directional velocity if c is
affected
asymmetrically by selfsynchronization disturbance.
The validity of the mass Equation (5) and the inertial property Equation (7)
propagates to
atoms, molecules and also to a solid object. The latter is regarded as
integral entity of stable
elementary particles.
Conclusion: Asymmetrical disturbance of the sefsynchronization around an
elementary
particle, a neutral atom, a molecule or a solid object will cause a change of
its gravito-inertial mass
according to Eq. (5) and a unidirectional non-inertial displacement according
to Eq. (7). From both
Equations it is evident that the common parameter c - speed of light should be
affected if
achieving an interaction with the Compton frequency vc = 1.236 x 1020 Hz,
which is one of the
basic parameters of the physical vacuum.
Now the question is how this super-high frequency could be reached. The answer
comes
from the unveiled structure and oscillating properties of the electron. It is
shown in BSM-SG,
Chapter 3 (also in Physics Essays, 16, No. 2, 180-195, (2003)) that the
electron possesses a
material structure of a cut toroid as a single turn coil with a radius - the
known Compton radius
and a small helical step responsible for its anomalous magnetic moment. Then
the electron's
material structure appears as a three body oscillating system exhibiting a
screw-like motion with
oscillation property characterized by two proper frequencies. The First proper
frequency of the
electron is the known Compton's frequency, while according to BSM-SG theory
the CL node
possesses the same Compton's frequency. The second electron proper frequency
is 3 times the
Compton's frequency and plays a role for the electron's spin. In such aspect
the moving and
oscillating electron has a preferable screw-like motion velocities defined by
its Quantum
Mechanical interaction with the physical vacuum. This QM interaction is the
strongest at electron
velocity ac = 2.188 x 106 m/s corresponding to energy of 13.6 eV. At this
velocity the oscillating
phase of the moving electron matches the CL node phase propagated with the
speed of light. Other
Quantum velocities are (ac/2) - corresponding to energy 3.41 eV, (ac/4)
corresponding to energy
of 1.51 eV and so on. The oscillating model of the electron explains quite
well all known
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properties of the electron including its anomalous magnetic moment, spin,
gyromagnetic factor and
the way it creates quantum orbits in atoms and molecules.
For accessing the Compton frequency a technical approach called a Heterodyne
method is
suggested. According to this method the Super-high Compton frequency of the CL
node
vc = 1.236 x 1020 Hz, which is a basic element of the underlying structure of
the Physical vacuum,
can be reached by the oscillating electrons, each one bound to a single
ionized atom.
The physical mechanism of Heterodyne method is illustrated by Fig. 1, where 1-
is the
trajectory of the single ionized atom, 2 - is the helical trajectory of the
bound electron, 3 is the
magnetic filed line of the electron moving in a helical trajectory, 4a and 4b
are electrodes on which
AC high voltage is applied. Considering a moving ion with a trajectory 1, the
bound electron will
make a helical trace 2. If the positive ion motion is reversible, the bound
electron will also make a
reversible helical motion. Since the helical step of the electron's structure
mentioned above is
much smaller than the electron's Compton radius the confined motion velocity
of the electron
moving on the helix 2 will be much greater than the ion velocity. This allows
the electron to move
in a helical trajectory with one of his quantum velocities corresponding to
energies of 13. 6 eV or
3.41 eV, while the velocity of the ion can be much smaller. It is well known
that the magnetic
moment of the electron is 658 times greater than the magnetic moment of the
proton and 981 time
greater than the magnetic moment of the neutron. Then the magnetic field of
the bound system of
single ion-electron will be predominated by the magnetic field created only by
the electron. The
magnetic field from the electron moving in a helix is additionally many times
stronger than if
moving with the same velocity in a straight line. Additionally the magnetic
fields of the
neighboring ion-electron pairs interact constructively. As a result, a large
number of ion-electron
pairs move in a cluster.
The described mechanism is achievable for actuator containing two electrodes
separated by
a proper gap and operated in a gaseous atmosphere with conditions for
ionization. Then one may
create an alternative electrical field by applying an AC high voltage in the
accessible RF range so
that the ion moves reversibly, while the bound electron moves in a helix with
one of its most
probable quantum velocity corresponding to energies of 13. 6 eV or 3.41 eV.
The reversible
motion of the electron under the apply AC field causing a flipping of the
electron spin. From a
point of view of the unveiled electron structure [8] the spin flipping is a
change of the phase of the
oscillating electron at Compton's frequency with 180 deg in respect to the
Compton's frequencies
of the CL nodes. At this particular moment a strong energy interactions takes
place between the
electron and the physical vacuum.
The practical realization of such process is a creation of neutral plasma
around a properly
design actuator. The physical process is characterized by the following
consecutive phases:
- ionization of neutral atoms or molecules
- ions get acceleration
- build up of ion-electron pairs, each one formed by a single-charge ionized
atom and a free
electron
- the ion-electron pairs are initially accelerated by the applied electrical
field acting initially
on the positive ions and after that guided by the common magnetic field
created by the bound
electrons
- the acceleration and motion of the electron-ion pairs is reversible in every
half cycle of the
applied AC electrical field
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The following considerations are dictated from the time duration and
efficiency of such
type of plasma:
- The reversible motion of the ion-electron pairs can be disturbed by
collision, so the process
needs reactivation
- The process is more effective for ions that contain lower number of protons
and neutrons
since the ratio of the electron to proton (neutron) magnetic moment ratio is
greater.
- The frequency of the applied AC field must assure that the ions are trapped
between the
electrodes.
- An external magnetic filed properly oriented in respect to the magnetic
field of bound
electrons might increase the efficiency.
The Heterodyne method is achievable in EM activated neutral plasma excited by
AC high
voltage or other means. A signature of positive ion-electron pairs is found in
the analysis of a large
number of experiments involving an EM activated neutral plasma. It is apparent
in experiments
using different gases and at different pressure range - from a vacuum to a
normal atmospheric
pressure and even overpressure. In many published experiments the researchers
point out that the
average electron velocity is in the range 3-10 eV, which is much lower than
the expected one and
they did not have an adequate explanation for this. In fact this is in a good
agreement;with the
predictions of the Heterodyne model, since the estimated average electron
velocity in fact is an
average value of the electron velocities involved in the ion-electron pairs
(energies of 13.6 eV and
3.41 eV) and some free electrons. The formation of ion-electron pairs must be
done frequently due
to unwanted collisions of ion-electron pairs with neutral molecules and other
ions. In such aspect it
is convenient to apply an AC HV filed which can be in the kHz frequency range.
Practically, the Heterodyne method can operate in wide range of pressure from
a few tors
to atmospheric and even above atmospheric pressure. The formation of ion-
electron pair clusters
helps to increase the effective free path. Nevertheless the effect strength is
reduced in the normal
atmospheric pressure due to losses from collisions and presence of negative
oxygen ions. The
efficiency is strongly dependent on the average free path between collisions.
The collisions
contribute to the significant fraction of the broad band high frequency
spectrum, which is
unwanted EMI noise. Only single ionized positive ion can participate in the
working ion-electron
pairs. Some negative ions significantly disturb the process. The selection of
working gas is also
important, as this is evident from the mentioned above considerations.
Massines et al. [12]
investigated an atmospheric glow discharge with different gases. Their
experimental results
completely agree with the mentioned above considerations for selection of the
working gas and
plasma reactivation. Some lab experiments also indicate that the efficiency
could be increased if
using a selected working gas with a lower ionization potential with a buffer
gas having a higher
ionization potential.
One additional important feature for increasing the efficiency of the SARG
effect was
predicted by the inventor when analyzing the dynamical and static behavior of
the CL node as an
element of the physical vacuum structure according to BSM-SG (Chapter 2). The
applied AC field
causes much larger CL node oscillation along the xyz axes than the
oscillations responsible for a
normal Zero-point energy. When a CL node is in a DC electrical field created
by a large number of
charge particles, its averaged central position is slightly displaced. If a DC
and AC fields are
simultaneously applied, they cause a CL node displacement plus dynamic
oscillations. Since the
displacement has a limit the combination of AC + DC field causes a nonlinear
effect, which does
not exists in a normal CL node oscillation. The nonlinear effect leads to
increased efficiency of
SARG effect, which means the synchronization disturbance that leads to
creation of mentioned
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above force filed is more effective. The inventor experimentally verified this
feature, not
envisioned so far in the prior art research.
Fig. 2 shows a simple plasma thrust actuator for demonstration of the SARG
effect,
comprised of a conductive body 5 covered with an isolation layer 6, a teflon
cap 7, a first electrode
8, a second electrode 9, and floating electrodes 10. The activated plasma is
observed as an
envelope 11 that may not have a uniform thickness. The thrust force is in
direction 12. At normal
air pressure the actuator is supplied by a high voltage AC field in order of
25 kV and adjustable
frequency in the range 2 - 5 kHz, combined with a DC field. In order to
eliminate the possible
effect of ion wind the actuator was enclosed in a transparent plastic cylinder
and hanged up on two
thin wires, which connect the electrodes 8 and 9 to the HV AC+DC power supply.
In order to
exclude a possible effect from asymmetrical radiation pressure due to emitted
FM radiation, the
cylinder was additionally enclosed in a metal shield, not shown in the figure.
The thrust force was
always in the direction 12. It is defined by the asymmetry of the plasma
envelope 11. Since the AC
frequency depends on number of design parameters including the type of the gas
and its pressure,
it must be adjusted until hearing a specific noise like a wind blow.
Fig. 3 shows the block diagram of the electrical circuit used for test of the
plasma thrust
actuator illustrated in Fig. 2. It is comprised of AC high voltage generator
14, a capacitor 15, a
resistor 16, and a high voltage rectifier 17 containing a number of diodes
shunted with high ohm
resistors and connected in series. By setting a proper value of the resistor
15 this circuit assures
that the necessary DC high voltage is always proportional to the magnitude of
the AC high voltage.
Fig. 4 shows the signal measured by antenna at 1.5 m distance from the plasma
thrust actuator,
where 18 is the AC HV frequency signal and 19 is the packet signal containing
a RF frequency in a
range from a few MHz to about 200 MHz. The RF signal is a result of collisions
between ion-
electron clusters with the free ions, atoms and molecules. For uniform plasma
discharge the RF
packet has duration much smaller than the half of the sinusoid. The experiment
is also
accompanied with a clear audible signal of a pure sinusoidal component
corresponding to the AC
frequency and a noise like from a wind blowing through an obstacle. The
blowing wind-like sound
is from the collisions between the reversible moving ion-electron clusters and
the air molecules.
The observed SARG effect in this laboratory experiment is weak due to the
following reasons,
predicted theoretically and confirmed experimentally:
- The atmospheric air is not the optimal gas mixture for the Heterodyne
method. Lower
atomic mass gas as Helium is much more effective, but it has a lower
dielectric strength. The
solution is to use lower atomic mass gas with a buffer gas having a higher
dielectric strength
- The SARG effect has a nonlinear dependence on the applied electrical field
and has a
bottom threshold limit. The applied field for the experimented test bed is
about 20 - 25 W. Higher
voltages require special laboratory environments.
- From the analysis of the CL node dynamics (BSM-SG, Chapter 2), in case of
applied
electrical field it becomes apparent that the force field should be
proportional to the HV in the
order of U2 to U3. Different researchers of plasma actuators with AC
activation also report a
similar range.
- From energetic point of view, the plasma activation by a sinusoidal AC high
voltage is
highly inefficient, because the actuator behaves as a capacitor load with a
negligible DC current
discharge. As a result, a large reactive power returns to the power supply and
dissipates as heat.
The theoretical predictions of the Heterodyne method, verified by experiments,
indicates that
instead of a full AC sinusoid only the initial activation slop of the AC high
voltage with a finite
time duration is necessary for creation of oscillating ion-electron pairs. The
finite time duration
CA 02638667 2008-08-26
depends on the working pressure. While the AC field provides this condition
every half cycle, it is
obvious that the unwanted reactive power could be more effectively rejected if
a feedback cut-off
is implemented at exact phase point of the activating AC voltage. One possible
way to provide
such cut-off is an AC HV source based on a Tesla coil, which incorporates a
spark gap in the
primary coil. The spark gap plays a role of a plasma switch that may cut-off
the unwanted parasite
feedback at required phase point of the AC cycle. Another option is using of a
Marx-bank
circuitry. Other AC HV circuits based on tyratrons or tyristors also could be
used with some
compromise on the power efficiency.
Fig. 5 illustrates another option of plasma actuator comprised of a conductive
body 20, isolator
caps 21 and 22, end side electrodes 23a and 23b, and a medium electrode 24
connected to the
conductive body 20, which may optionally have an isolating cover like the
actuator in Fig. 2. The
actuator has two opposite plasma sections between the two opposite electrodes
23a and 23b and
the medium electrode 24. In this case the middle of a HV transformer 25 is
connected to the
electrode 24. The diodes 26 and 27 assure alternative operation of the
opposite plasma sections,
while the reactive energy from each one section will be transferred to the
other one by the circuits
28 and 29 consisting of an inductance, capacitor and diode connected in
series. This transfer must
occur at proper point of the sinusoid of the activating AC voltage, so it puts
more severe
constraints to the activating AC frequency, which depends on the working gas
and the atmospheric
pressure. The means assuring simultaneous DC high voltages to both sections
are not shown in
Fig. 5, but they can be obtained in a similar way as shown in Fig 3. This type
of plasma actuator
must assure higher power efficiency in comparison with the actuator shown in
Fig. 2 supplied by
the circuit shown in Fig. 3.
The creation of a protective field shield around a spacecraft is envisioned
from the analysis of
the dynamical behavior of the CL nodes in applied electrical magnetic and EM
fields, according to
the BSM-SG theory. The CL space model of the physical vacuum predicts also an
existence of
compress-like waves, different than the known EM waves. A number of
theoreticians derive such
waves by using the original Maxwell equation based on quaternions [ 13,14].
Such waves are
confirmed also experimentally and they are known in the prior art as scalar or
longitudinal waves
[15]. They are able to carry much greater energy than the ordinary EM waves.
The pioneer of
generating longitudinal waves is Nikola Tesla, who provided means for their
generation in tens of
patents and lectures in the period from 1893-1913 [16]. The longitudinal waves
obtains clear
physical explanation from a point of view of BSM-SG theory: The EM waves
involve oscillations
along xyz axes of the CL nodes, while the longitudinal waves involve
oscillations along abcd axes.
The stiffness along abcd axes is thousands times stronger than the stiffness
along the xyz axes, so
the longitudinal waves may carry much larger momentum than the EM waves. One
additional
feature of the longitudinal waves, also envisioned by BSM-SG theory, is that
they may propagate
much faster than the speed of light if the CL nodes in their path are
synchronized. From the
analysis in BSM-SG theory (Chapter 2, section 2.10.4) it becomes evident that
within the photon
wavetrain the CL nodes are synchronized. This means that within the wavetrain
one can propagate
information and energy much faster than the velocity of light. This is
confirmed by some
experiments called "quantum teleportation" which demonstrate transfer of
information much faster
that the speed of light. The analysis of the methods for producing of
femtosecond laser pulses from
a point of view of the BSM-SG also unveils a superluminal effect of squeezing
the extending beam
path with a finite length into a strong femtosecond pulse. In the case of EM
wave propagation the
CL node dynamics is similar like in the photon wavetrain with the difference
that there is not a
transverse boundary limit as in the wavetrain of the photon.
11
CA 02638667 2008-08-26
The experiments of N. A. Kozirev, provided in the period 1977-1982 [17,18] and
later repeated
by other Russian scientists [19] are known in Russian literature as Kozirev's
effect. In fact Kozirev
experiments exhibit two major phenomena. One is a reduction of the
gravitational mass of solid
object by a small fraction after some mechanical (vibrational) or electrical
treatment. He also
found that the weight restoration takes a finite time in order of minutes. The
other phenomenon
found by Kozirev is a determination of an instant positions of some distant
stars by detection of
non EM wave from them traveling billion times the speed of light. This
superluminal velocity is
detected also by Gregory Hodowanec during a moon eclipse [20]. Kozirev found
also that
superluminal non-EM waves exhibit a gravitational effect - they affect the
position of a
supersensitive weight balance used as a detector [17]. Finally numbers of
experiments published
recent years in peer-reviewed journals demonstrate a superluminal propagation
of waves known as
X-waves in a closed ranged field of a few wavelengths. D. Mugnai, A. Ranfagni
and R. Ruggery
[21 ] demonstrated superluminal propagation of microwave packets at 8.6 Ghz
(wavelength of 3.48
cm) up to a distance about 1 m with average superluminal velocity greater than
the light velocity
by 5.3%. The authors express the idea that there is not a theoretical limit
for superluminal
propagation at longer wavelengths
Based on of the prior art experiments and observation of some phenomena
analyzed from the
point of view of BSM-SG, I came to the following conclusion:
It is possible to create an artificial boundary on the propagated EM wave with
unique
properties of protective field shield. I suggest the following technique:
- Emission of EM wave packets of stable frequency in the RF or microwave
spectral range
- Emission of a delayed strong short EM pulse with a large dU/dt and the same
aperiodic
frequency but with higher order odd harmonics with the same phase
- The EM wave packet and the strong EM pulse must be emitted from one and a
same
location and from a common or a separate circular dipole antennas with length
equal to one or
multiple wavelengths.
Fig. 6 illustrates the timing diagrams requirements, where 30 is the EM wave
packet with a
duration tEM and 31 is the strong EM pulse emitted at time td after the front
end of the wave packet
33. The shown waveforms must be repeated with a period larger than tEm.. When
emitted by a
proper selected means and during the EM wavepacket, the strong EM pulse will
propagate at the
close range field with a velocity exceeding the light velocity, an effect
called superluminal
propagation.
According to the above-mentioned conclusions about the superluminal
propagation of a
strong EM pulse along the path of the EM wave packet, it is obvious that the
delayed strong pulse
will propagate by the same path of the EM wave, but overriding it until
reaching the front end of
that packet. If the propagation time of the EM wave packet to this point is t,
the time propagation
of the superluminal pulse is (t - td). From this moment the conditions for the
superluminal
propagation of the strong pulse becomes suddenly different and a kind of
reflection effect will
occur. This will affect also the further propagation of the EM wave packet and
its energy will be
deposited at this moment in a thin layer, forming something like a compressed
zero point energy of
the physical vacuum. If assuming for simplicity that the EM wave packet and
the strong pulse are
emitted by a spherical emitter, the aforementioned layer will correspond to a
spherical surface with
a radius R according to Eq. (8)
R - VXtdC (8)
VX-c
12
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where: VX is the superluminal velocity of the strong EM pulse in a field
distance of a few
wavelengths of the EM wave packet frequency, c - is the light velocity
For the described case of emission of a strong EM pulse during the emission of
an EM
wave package, the value of VX must be determined experimentally, since it may
appear much
larger than the experimental setup reported by D. Mugnai et al [21 ].
The deposition of the whole energy of the EM wave packet on the spherical
surface with a
radius R and small thickness means that the selfsynchronization of this
spherical surface will be
disturbed or rearranged. It was theoretically predicted by BSM-SG theory and
confirmed by some
observed phenomena that the disturbed or rearranged selfsynchronization needs
a finite time for
self-restoration. If the time between the emitted EM wave packets is shorter
than the self-
restoration time, many wavepackets will dissipate their energies until some
energy balance occur.
The disturbed selfsynchronization of the CL nodes in this spherical surface
will affect the gravito-
inertial mass of the dust particles, while the dissipated energy will create
some kind of protective
field shield against micrometerorites. According to the BSM-SG theory (Chapter
3, section
3.12.2.A) the disturbed selfsynchronization will affect the conditions for the
quantum orbits and
consequently it will cause a weakening of the atomic and the molecular bonds
in the solids.
Therefore the micrometeorites moving with large velocities might be
disintegrated into smaller
fractions.
When the field shield is created at conditions of normal Earth atmospheric
pressure, part of
the emitted EM energy will dissipate within the volume of the sphere due'to
partial ionization of
the gas molecules. However, the protective field shield will be more efficient
in highly rarefied
atmosphere. The analysis predicts the possibility for creation a field shield
over a spacecraft
moving in a deep space, since the released by the spacecraft gas mixture for
the necessary plasma
may provide also the necessary conditions for a field shield up to some
radius. Nevertheless, the
described effect might be used not only for a spacecraft protection. One may
speculate that if
applied in a larger scale in a planet without or with a rarefied atmosphere,
the protective field
could be able to create a spherical dome inside of which an artificial
atmosphere could be created.
The field shield in this case will serve as a stop boundary of the artificial
atmosphere in order to
not escape into the deep space. In such case an artificial colony could be
created for example on
the Moon or on Mars.
Fig 7 shows an example of the electrodes configuration for means assuring a
protective
field shield, where 32 is a circular dipole antenna for emission of the EM
wave packets, 33 is a
sectored ring antenna for emission of the strong EM pulse, and 34a and 34b are
spherical
electrodes with a common connection serving as a as virtual ground for the
sectored ring antenna
33. Since the emitters does not have a spherical emission diagram, the
protective field shield will
be still spherical but with strength stronger at radial directions where the
dipole emission is
stronger. This is illustrated by the density of the dashed line showing the
protective field shield 36,
while 35 shows the emission diagram of the dipole antenna 32. The dipole
antenna 32 and the ring
antenna 33 are with the same diameter, and their circumferences are equal to
the wave packet
wavelength. The virtual grounds for both antennas are completely isolated.
This measure not only
protects them from mutual interference but also allows operation with larger
energy according to
the Nonlinear Oscilator-Circuit Theory published by T. W. Barrett [22]. The
ring antenna 33 is cut
al least in one place, so it contains one or more gaps. This measure prevents
it to behave as a short
turn when the wavepacket is emitted by the dipole antenna 32. However, when
emitting a strong
EM pulse, the antenna 33 behaves as a single ring, since the gaps are of such
length that to be
crossed by sparks appearing during the strong pulse. The ring antenna 33 can
be used also for
13
CA 02638667 2008-08-26
activation of the neutral plasma between it and the electrodes 34a and 34b for
creation of SARG
effect. Such twofold function of the antenna 33 allows better relation between
the necessary
propulsion force field and the protective field shield. For this purpose,
however, a more complex
electrode configuration is required, as it will be shown below.
Fig. 8 shows the shape of a spacecraft for interplanetary flight with the
external functional
elements of its propulsion system, where 37 is a spacecraft body with a thick
isolation layer for
withstanding high voltage potentials, 32 is a dipole antenna, 33 is a ring
antenna, 38 is an upper
spherical electrode, 39 is a set of three bottom spherical electrodes at 120
deg, 40 is a set of
isolated electrodes, and 41 are set of portholes for preactivated plasma. The
purpose and functions
of the dipole antenna 32 and the ring antenna 33 are previously described by
the help of Fig. 6 and
Fig. 7. The oval shape electrodes 38, 39 and the ring antenna 33 are for EM
activation of neutral
plasma 42 around the spacecraft. The set of electrodes 40 is comprised of one
or more narrow flat
annular electrodes, completely isolated and not electrically connected to any
activating circuit.
Their functionality is similar to the electrodes 10 in Fig. 2 - to guide the
plasma near the spacecraft
body. The activation circuit for the bottom electrodes 39 is a three-phase AC
high voltage system.
based on Tesla coils the secondary of which are of Y type of configuration.
The three phases are
connected in series with attenuator-phase shifters to the three bottom
electrodes 39, while the
common point of the Y type is connected to the ring antenna 33. Separate
rectifiers for each phase
assure the necessary DC high voltage for the electrodes 39. The top electrode
38 obtains AC+DC
high voltage from a separate single-phase Tesla coil [ 16], also in series
with an attenuator. The
common point of the Y type 3-phase Tesla coil and the second Tesla coil are
connected together
forming a "virtual ground" to which the ring antenna 33 is connected. A
preferred erribodiment of
the Y-type and single phase Tesla coils with attenuator-phase shifters is
shown in Fig. 10. The
dipole antenna 32 for emission of EM wave packets is supplied by a separate
circuit, which does
not have any common point with the circuits connected to the electrodes 33, 38
and 39. Instead of
Tesla coils with air gaps other type of circuits capable of generating high
voltage pulses with short
duration could be used. The portholes 41 serve to release a proper gas mixture
as preactivated
neutral plasma. The portholes are outputs of plasma guide tubes connected to
an internal plasma-
activating unit or plasma dispensers. The means for creation of neutral plasma
are known from the
prior art. The preactivated plasma removes the requirement for plasma
ionization by the electrodes
33, 38 and 39, so they can operate at lower AC+DC high voltages. When the set
of electrodes 38,
39 and 33 are supplied by AC+DC high voltages with proper magnitude and phase
an asymmetric
plasma envelope 42 appears around the spacecraft. According to SARG effect,
this will permit
creation of a force field in any desired direction. Additionally the gravito-
inertial mass of the
spacecraft can be reduced even in a motionless position if the activated
plasma envelope is
symmetrical. In this case the debit of the preactivated plasma must be
increased. From this
condition the spacecraft could be accelerated sharply from a stationary point
or can make a sharp
turn during a straight motion by changing the symmetrical to asymmetrical
plasma envelope. This
option allows to accelerate the spacecraft with less energy because at the
beginning of acceleration
its mass is reduced. The gas mixture must contain a working gas of low atomic
number and a
buffer gas with larger dielectric strength.
The AC high voltage between the electrodes 33, 38, 39 may not be continuous
but in
packet. The gravito-inertial effect shows sustainability for a finite time
after the cause is removed.
The effect has been observed by Kozirev [17]. He weighted solid objects, then
vibrated them and
weighted again. The vibrated solid objects lost a small fraction of their
weight and their normal
weight was restored exponentially for minutes. The restoration time he found
does not depend on
14
CA 02638667 2008-08-26
the weight of the object but on its density. This is in good agreement with
the BSM-SG
explanation, that the disturbed selfsynchronization needs a finite time for
its restoration and that
the dens material affect stronger the CL space inside of the body - a micro
effect of General
Relativity. The finite time restoration of the CL nodes selfsychronozation is
convenient to combine
the pulse type activation of the surrounding plasma with the creation of the
field shield, which also
require repetition of the EM wave packets and the strong superluminal pulse.
The other effect
found by Kozirev - the dependence of the weight restoration time from the
object density allows
selecting the proper material for shielding the crew from the effect of the
spacecraft acceleration.
When moving in a planetary gravitational field the crew will feel almost a
normal gravitational
field, but when the spacecraft is far from any planet only the local star
gravitational field will be
felt.
During landing or take-off from a planetary ground the electrodes 39 must be
at some
distance from the ground in order to avoid short circuit or parasite
discharge, so retractable legs are
needed. The protective field shield must not operate during the landing or
take-off, so the dipole
antenna 32 must not be supplied in these cases. During maintenance, repair or
staying on the
ground the electrodes 32,36,38 and 39 must be grounded for human safety.
The portholes are connected with plasma guides inside of the spacecraft and
they carry the
preactivated plasma. They are known from the prior art. Particularly the
configuration of S.
Okazaki and M. Kogoma [18] is suitable.
A spaceship for a long range travel with a propulsion system based on a SARG
effect must
have different configuration because it will travel a.long time in a space
with a greatly reduced
gravitational field. The side and the oblique view of the preferable
embodiment of such spaceship
is shown respectively by Fig. 9.a and Fig. 9.b, where 43 is the overall shape
of the spacecraft, 44
and 45 are respectively front and back end thrust actuators, and 46 is a three
set rows of side thrust
actuators at angle 120 deg between the rows. The preferable motion of this
spaceship is along the
axes 47, in which case the thrust force is assured by the actuators 44 and 45,
creating respectively
plasma 48 and 49. If the plasma 48 is stronger than the plasma 49 the motion
is from left to right.
When moving in a strong gravitational field, the sets of side actuators 46
must also be activated.
The two sets of actuators 46 at angle of 120 deg are capable of keeping a
proper orientation in a
gravitational field. In a long range travel the gravity from the star system
is negligible for the crew,
so it is necessary to create it artificially. This can be done by rotation of
the spaceship around the
axes 47. The necessary rate of rotational can be achieved by a proper phase
activation of the 3 sets
of side actuators 46, as they are shown in Fig. 9.b. They create side plasma
50. This type of
spaceship is not suitable for landing and for this purpose it may carry disc-
shape spacecrafts as one
illustrated by Fig. 8. It may not have maneurability of the disk-shape
spacecraft and must contain a
thick shield for protection from harmful cosmic radiation by classical means.
Fig. 10 shows a proffered embodiment of the circuit that supply the AC+DC high
voltage
for the three electrodes 39 of the spacecraft shown in Fig. 8 and each triads
of the side actuators 46
of the spaceship shown in Fig.9 a, b. The circuited is comprised of a low
voltage AC power supply
51, a pulse transformer 51, a chock 61 a spark gap 53, a group of three
primary coils 54 in series
with capacitors 55, the said group connected in a series with the spark gap
53, a second group of
three secondary coil 56 in series with a capacitors 57, said secondary group
connected from one
side to the electrodes 39 and from the other through three groups of parallel
capacitors 58 and 59
to a common point 60, said the elements 57, 56,58 and 59 form Y type three-
phase system. Each
electrode 39 is connected by a parallel group of resistor 16 and rectifier 17
to the common point of
the Y type system 60. The group of elements 16 and 17 serve to supply the
electrodes 39 with a
CA 02638667 2008-08-26
DC high voltage witch is proportional to the AC high voltage. The number of
winding of 56 is
much larger than the number of windings of 54, according to the Tesla coil
considerations in order
to obtain the necessary AC high voltage. The elements 59 are high voltage
variable capacitors,
which serve to adjust the phase difference between the AC high voltages
provided to the electrodes
39. They are shunted with capacitors 50 to assure a safety limit in the
regulation of the phase,
which is accompanied also with a change of the magnitude, causing some
asymmetry of the central
point 60 in respect to the electrodes 39.
The single-phase Tesla coil for supply the AC+DC high voltage to the top
electrode 38 is
comprised of a spark gap 62, a primary coil 63 a secondary coil 64, connected
from the bottom
side through capacitors 65 and 66 to the middle point 60 of the Y-type three-
phase Tesla coil, end
connected to the electrode 38 vias capacitor 67. The rectifier 17 through the
resistor 16 assure the
necessary DC high voltage potential for the electrode 38.
Let not consider at first the effect of the bottom electrodes 39 on the
spacecraft showsn in
Fig. 8. If the regulators 58 of the three phase shifters-attenuators are at
equal calibrated positions
the phase difference between the 39 electrodes is 120 deg and the voltage
magnitudes between
them and the point 60 are equal. The plasma surrounding the spacecraft at the
bottom is uniform. If
the phase difference is misbalanced by regulators 58 the voltage magnitudes
become also different
and the plasma envelope on the spacecraft bottom is asymmetric. This will
invoke a force field in
the direction of the stronger to weaker plasma envelope. When considering the
function of the top
electrode it is evident that a force field could be created at any desired
direction including a
possibility to tilting the spacecraft.
The described propulsion method based on the SARG effect is not suitable for
application
in commercial aircrafts flying in Earth atmosphere because of the following
reasons:
- the effect creates EM noise and may affect the communication systems within
some range
- staying in proximity to the spacecraft during the landing or takeoff is
dangerous for humans
and live species.
The suggested propulsion method is intended only for spacecrafts capable of
leaving
Earth atmosphere and traveling to other planets or star systems. A spacecraft
with such propulsion
will greatly overperform the rocket missions based on ajet propulsion system.
I claim:
1. A method and apparatus for a spacecraft propulsion with a field shield
protection, wherein
said method is achievable by envelope of neutral plasma activated by AC and DC
EM
fields and simultaneous emission of EM wave packet and strong EM pulses with
selected
time sequence, said method comprising steps of:
releasing of preactivated plasma of gas mixture composed of working gas and a
buffer gas,
creation of envelope of electromagnetically activated plasma around the
spacecraft by
a controllable set of AC and DC electrical fields around the spacecraft from
at
least 5 electrodes assuring a necessary asymmetry of the plasma envelope,
where
the said DC electrical fields are kept proportional to the applied AC fields,
emission of EM wave packet and strong EM pulse with a strong space and time
correlation between them,
16
CA 02638667 2008-08-26
said apparatus for a spacecraft propulsion with a field shield protection
comprising of:
a spacecraft body without external sharp edges when in operational mode,
a set of at least three bottom oval shape electrodes, each one connected
simultaneously to a Y type type three-phase AC high voltage system with a
proper frequency and means for phase and amplitude control,
at least one top electrode connected simultaneously to a single phase AC high
voltage
system and to a DC high voltage,
said single phase high voltage system having a common virtual ground with the
central point of the said three-phase AC high voltage system,
separate DC high voltage circuits for each of the bottom and top oval shape
electrodes, obtained by rectifying a fraction of the AC high voltages that
supply
those electrodes,
one ring electrode comprising of one or more sections separated by one or more
gaps
whereas at lease one or these sections is connected to the virtual ground
point of
the said three-phase AC high voltage system,
one circular dipole antenna connected to a generator of EM wave packets with a
circumference length of the dipole antenna equal to one or multiple
wavelengths
of the said EM wave packet,
a set of portholes on the spacecraft body for releasing of preactivated plasma
from a
gas mixture, where said gas mixture is comprised of working gas with a low
atomic number and a buffer gas with a higher dielectric strength.
2. The invention of claim 1, wherein the propulsion force field is a result of
gravito-inertial
effect invoked by applying of asymmetrically activated neutral plasma around
the
spacecraft.
3. The invention of claim 1, wherein said protective field shield is a result
of mutual
interaction between the emitted EM wave packet and the strong EM pulse
possessing a
superlumainal behavior with proper time correlation between them and a proper
period, so
an effect of energy dissipation occurs on the on molecular species or dust
particles in the
boundary of finite thickness serving as a protective shield.
4. The invention of claim 1, wherein said Y type three-phase AC high voltage
system is part
of a poly-phase Tesla coil system, in which the secondary windings are
connected as Wye
type, while the primary windings are connected in series with capacitors and
one spark gap
or other type of circuit interrupter.
5. The invention of claim3, wherein said strong electromagnetic pulse
possessing
superluminal behavior in a near field of a few wavelengths is experimentally
confirmed.
17
CA 02638667 2008-08-26
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Search keytivords in google and youtube: SARG effect, SARG Antigravity.
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