Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is smaller than another ramjet on the right side of the tube 3. The difference in size between the ramjets makes the ramjet 6b exert a weaker force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. A fin 6c is also able to cause the rotate-able tube 3 to rotate during flight. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate.

Abstract: A lighter-than-air aircraft is propelled via a bending-rotating tail whip. Two actuating areas located on opposite sides in a rear area of a lifting gas body are shortened by activated actuators. A vertical plane of symmetry of the lifting gas body and thus, the lifting gas body itself, are pivoted in an area of bending zones about angles a and ?. An activated state exists when the actuator performs work for propelling the aircraft. Propulsion can be provided by deformation of the lifting gas body. Changes in direction can also be effected by asymmetrical sequences of movements.

Abstract: An engine system for an aircraft capable of operating in a helicopter-type flight mode and a fixed-wing flight mode and is capable of transitioning between those flight modes while in-flight includes first and second engines, and a ducting assembly. The ducting assembly includes a first exhaust subassembly in fluid communication with the first engine and a second exhaust subassembly in fluid communication with the second engine. The first exhaust subassembly permits fluid transfer substantially independent of fluid transfer within the second exhaust subassembly.

Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.

Abstract: The invention relates to a plasma based aircraft possessing a magnetic field, and, a huge plasma vortex. Said craft is tubular in shape. Said craft has a vast array of capacitors. The craft has a proton accelerator, plasma guns, diversion devices. Said craft will approach the speed of light. Said craft obtains fuel direct from an atmosphere or a radiation produced atmosphere in space, at no cost. This craft can travel to a g k star for only the cost of construction of craft. This invention is comparable to the discovery of fire insofar as man's future is concerned, particularly in view of our climate change, and a recent near impact from an asteroid—which would have put us within an ice age. The craft has three on-board escape craft. The craft is capable of producing plasma vortices within an electromagnetic field approaching the speed of light. Said field is an inhomogeneous, diamagnetic, orbiting plasma field with a magnetohydrodynamic electrically conducting plasma current.

Abstract: The present invention describes lighter-than-air vehicles. An exemplary embodiment of the present invention provides a lighter-than-air vehicle having a payload module, the payload module including an engine. Furthermore, the lighter-than-air vehicle includes a non-rigid envelope in communication with the payload module. The lighter-than-air vehicle also provides a propulsion system that includes a plurality of thrusters, the thrusters positioned substantially near the equatorial plane of the non-rigid envelope. In an alternative exemplary embodiment, the present invention provides a lighter-than-air vehicle comprising a payload module and a non-rigid envelope in communication with the payload module. Furthermore, the lighter-than-air vehicle includes a hydraulic propulsion system in communication with the non-rigid envelope and the payload module.

Abstract: The invention relates to an aircraft having a first propulsion unit with an air inlet above the fuselage of the aircraft and a second propulsion unit with an air inlet below the fuselage of the aircraft, the fuselage of the aircraft having recesses for receiving the propulsion units which are arranged such that the first and the second propulsion unit are arranged above one another in the plane set by the longitudinal and vertical axis of the aircraft. The propulsion unit comprises an engine, a housing having an air inlet, devices for the releasable fastening of the propulsion unit to the fuselage of the aircraft as well as devices for establishing a releasable connection of electric supply and data lines as well as fuel lines between the propulsion unit and the fuselage of an aircraft.

Abstract: A device for producing a net force against a base comprising a mass change object, an accelerator, a power source operatively connected to the mass change object and configured to selectively apply to the mass change object (1) a mass-increasing waveform, characterized in that the time rate of change of the power of the mass-increasing waveform is positive, and (2) a mass-decreasing waveform, characterized in that the time rate of change of the power of the mass-decreasing waveform is negative; the power source being configured to apply the mass-increasing waveform to the mass change object when the acceleration of the mass change object has at least a component opposite to the net force direction, and to apply the mass-decreasing waveform to the mass change object when the acceleration of mass change object has at least a component in the net force direction; wherein the mass-increasing waveform is a different waveform, as a function of time, than the mass decreasing waveform.

Abstract: The present invention relates to an aircraft and to a method of getting the aircraft onto station. According to the invention, said aircraft (1) includes propulsion means (2) capable only of enabling said aircraft (1) to move and to orient itself at high altitude, and said aircraft (1) is taken to its station in the high atmosphere, in particular in the stratosphere, by means of an independent transporter (3).

Abstract: An engine system for an aircraft capable of operating in a helicopter-type flight mode and a fixed-wing flight mode and is capable of transitioning between those flight modes while in-flight includes first and second engines, and a ducting assembly. The ducting assembly includes a first exhaust subassembly in fluid communication with the first engine and a second exhaust subassembly in fluid communication with the second engine. The first exhaust subassembly permits fluid transfer substantially independent of fluid transfer within the second exhaust subassembly.

Abstract: A multi-modal forced vortex device is described having a top plate and a side wall creating a partially enclosed volume. The top plate includes one or more adjustable fluid openings to permit, or restrict, fluid flow into and out of the partially enclosed volume. Rotating blades housed within the partially enclosed volume are manipulated (through control of their pitch and, possibly, their speed) in conjunction with the adjustable fluid openings to generate a variable magnitude attractive force in a first mode, a variable magnitude down or pushing force in a second mode, a variable magnitude up or lifting force in a third mode or variable magnitude yaw, pitch and roll forces in a fourth mode.

Abstract: An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine is adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to the aircraft. At least one of the pulse detonation engines is movably configured for altering a direction of the thrust force relative to the airfoil.

Abstract: A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed in the body. The control unit generates signals controlling an actuation of the attitude control mechanisms and the multi-pulse motor to initiate a follow-on burn of the multi-pulse motor to effect a maneuver directed by the actuation of the attitude control mechanisms. The method includes conserving a second burn of a dual pulse motor until target acquisition; acquiring a target; actuating a attitude control mechanism for the flight vehicle to alter the flight vehicle's heading; and initiating the second burn.

Abstract: A propulsion system is disclosed that uses microwaves originating from a ground-based or on-board source to provide energy for propulsion. The energy produces thrust by coupling into a propellant via a microwave absorbent heat exchanger, and by subsequent conversion of the propellant thermal energy to kinetic energy through a thrust converter or nozzle.

Abstract: A new method is described to produce useful electrical energy from DC electrostatic fields using a pyramid-shaped capacitor. The system uses no moving parts and no mechanical energy is introduced. Also, when a pyramid-shaped electrode is charged with DC high voltage, a propulsive force is generated. This will allow the manufacture of vehicles capable of levitation and flight.

Abstract: Provided is a disc-type jet turbine engine with controllable and rotational discharge ports at two sides of a discharge chamber, a fuel tank, and an operation lever connected with the discharge ports. The rotor shaft of the jet turbine engine is connected with a start-up electrical motor through a clutch and with a fuel pump through a gearbox. The fuel nozzle of the engine is connected with the fuel tank via the accelerator control valve and the fuel pump. The operation lever controls the clutch. The handle of the operation lever is provided with an electrical switch, a direction controller and an accelerator controller. The switch is electrically connected with the start-up electrical motor, the accelerator controller is connected to control the accelerator control valve, and the direction controller is connected with the discharge ports. Around the combustion chamber is an air-flow guide chamber having an air cooling and heat-insulate layer.

Abstract: A Solid Oxide Regenerative Fuel Cell (SORFC) or a Solid Oxide Fuel Cell (SOFC) is incorporated into an electrically powered airplane to provide either regenerative or primary electrical energy. The SORFC, the SOFC, or any other suitable fuel cell within an airplane may also be used to heat payload or equipment within the airplane. The SORFC is not only capable of generating electrical energy from fuel and a suitable oxidizer, but can also generate fuel through electrolysis of oxidized fuel. Thus, the SORFC system powering an airplane can obtain oxygen oxidant reactant from the air and avoid the complexity, weight, volume, and cost associated with oxygen storage.

Abstract: A nacelle (55) for a gas turbine engine (10), the engine (10) comprising accessories (34) mounted to a fan casing (28) and a core engine (9), the nacelle (55) substantially surrounds the engine (10) and comprises an intake (12) and a thrust reverser unit (31). The thrust reverser unit (31) is formed by two generally C-shaped portions (31a, 31b). The thrust reverser unit (31) is openable to provide access to the accessories (34) and the core engine (9). The nacelle (55) further comprises a fan containment casing (33) that is integral with the intake (12).

Abstract: The present invention includes a method for a dual-mode propulsion system. During the first mode of operation, intake air is liquefied through a cooling heat exchanger and condenser using a combination of stored liquid hydrogen (LH2) and stored liquid nitrogen (LN2) as coolants. The liquefied air is then separated into separated liquid oxygen (SLO2) and separated liquid nitrogen (SLN2), which may contain molecules of each other or other elements commonly found in air. The stored liquid nitrogen is replaced with SLO2, while the SLN2 is pumped back through the system with the stored nitrogen in a regeneration process. The SLN2, LN2, and LH2 become gaseous as they pass through the condenser and heat exchanger and are burned in the dual mode rocket thrust chamber to produce thrust. In the second mode, the same thrust chamber is operated as a liquid hydrogen-oxygen rocket, where the liquid oxygen is the SLO2 collected during the first mode.

Abstract: A control system for a flying vehicle in an atmospheric environment, the vehicle having an aerodynamic shape including a front end and a rear end including a plurality of attitude control jet nozzles spaced outward from the vehicle near the rear end of the vehicle or a trailing edge of a vehicle part; and a generator for providing a low mass flow of a fluid through the attitude control jet nozzles to create an area of high pressure immediately forward of the nozzles and adjacent the flying vehicle, wherein the location of the attitude control jet nozzles is so close to the rear end of the vehicle that any area of low pressure created by the low mass flow of fluid through the attitude control jet nozzles does not contact the vehicle.

Abstract: An unbalanced gyroscopic apparatus is disclosed for producing unidirectional thrust without having to interact with an external gas, liquid, or solid mass. The technique is based on the controlled transitions of an unbalanced spinning mass between two stable unbalanced weight states resulting in a net unidirectional thrust at the spin axis. In one existing embodiment, an apparatus with an attached body can be propelled up a planar incline “sliding” uphill against terrestrial gravity. In another embodiment, multiple pairs of synchronized and mirror-image, unbalanced gyroscopic assemblies are combined as one apparatus and attached to a body with the potential to propel it in any direction, including defeating gravity completely without interaction with gas, liquid, or solid mass or without use of propellants.

Abstract: A means to use the natural forces of nature when correctly understood and applied to move personnel and objects from Earth's surface to outer space using a conduit with valves, access air locks, support & stabilizing means, to redirect and throttle naturally occurring forces. A magnetic field may also be used. The magnetic field may be applied parallel or longitudinal to the conduit. “Outer space lake substance” Redirecting Means may be utilized with the conduit in order to assist in moving a vessel with personnel or objects to or from outer space.

Abstract: A mounting arrangement (46) for mounting a turbofan gas turbine engine (10) on an aircraft pylon (44). The gas turbine engine (10) comprises a core engine (24) having a core engine casing (26). The mounting (46) comprises a first mounting (48) for mounting the core engine casing (26) on the pylon (44) and a second mounting (50) for mounting the core engine casing (26) on the pylon (44). The first mounting (48) comprises a first hinge adjacent (52) the core engine casing (26) and a second hinge adjacent (54) adjacent the pylon (44). The first hinge (52) is arranged parallel to the axis (S) of the gas turbine engine (10) to form a roll hinge. The second hinge (54) is arranged in a plane perpendicular to the axis (S) of the gas turbine engine (10) to form a pitch hinge. The second mounting (50) comprises a third hinge (56) adjacent the core engine casing (26) and a fourth hinge (58) adjacent the pylon (44).

Abstract: This invention relates generally to method and apparatus for solar-boost assist and solar-sail assist by a mini-optics light concentrator system utilizing a dynamic ensemble of mini-mirrors. In the boost phase of a rocket ship launch, the system focusses solar energy into the rocket chamber to raise the temperature of the propellant and increase the impulse. In the mid-course phase, the system focusses solar energy onto the rocket's solar sail to increase the thrust. In both cases, the system reduces the weight of the rocket by providing a weightless source of thrust.

Abstract: A variable cycle propulsion system for a supersonic airplane comprises at least one engine capable of generating thrust for flight at supersonic speeds together with at least one auxiliary propulsion assembly that is separate from the engine and that is capable of generating additional thrust for takeoff, landing, and flight at subsonic speeds. The auxiliary propulsion assembly does not have a gas generator and means are provided for transmitting a fraction of the mechanical power produced by the engine to the auxiliary propulsion assembly in order to enable it to generate the additional thrust for takeoff, landing, and subsonic cruising flight. Means are provided for decoupling the mechanical transmission means for supersonic cruising flight.

Abstract: A concept of design rotary and linear engines pursuing increasing effectiveness by employment centrifugal force is creating by laminar movement whole working substance in rigid walls channel:

Abstract: A new method is described to produce useful electrical energy from DC electrostatic fields using a pyramid-shaped capacitor. The system uses no moving parts and no mechanical energy is introduced. Also, when a pyramid-shaped electrode is charged with DC high voltage, a propulsive force is generated. This will allow the manufacture of vehicles capable of levitation and flight.

Abstract: A lift-providing unit for lifting and steering a platform including two weight units disposed at opposite ends of a rotating armature, the weight units being capable of generating a recoil or an impact force. Lift is provided by the recoil or impact force multiplied by the weight and velocity of the incoming mass on the rotating armature.

Abstract: A power generation system comprises an internal housing. The housing has a top portion, a bottom portion and a peripheral sidewall. An external housing is provided. The housing is coupled to and receives the internal housing. The housing has an upper lip, a lower lip and a smooth outer edge. The upper lip is spaced from the internal housing to allow the flow of air into the external housing. A rotary pump is comprised of an upper washer and a lower washer. Fins are provided between the washers. The washers form upper and lower surfaces. Fins are coupled to both the upper and lower washers. Each fin is curved such that when rotated the rotary pump draws air into the external housing from the upper lip and pushes it past the lower lip and out of the external housing to life the system.

Abstract: An unbalanced gyroscopic apparatus is disclosed for producing unidirectional thrust without having to interact with an external gas, liquid, or solid mass. The technique is based on the controlled transitions of an unbalanced spinning mass between two stable unbalanced weight states resulting in a net unidirectional thrust at the spin axis. In one existing embodiment, an apparatus with an attached body can be propelled up a planar incline “sliding” uphill against terrestrial gravity. In another embodiment, multiple pairs of synchronized and mirror-image, unbalanced gyroscopic assemblies are combined as one apparatus and attached to a body with the potential to propel it in any direction, including defeating gravity completely without interaction with gas, liquid, or solid mass or without use of propellants.

Abstract: This invention relates to a magnetic vortex generator which has the ability to generate negative mass and a negative spring constant which, according to Einstein's General Theory of Relativity, is required in order to create a stable wormhole between our space and hyperspace. Two separate, but electrically connected, toroidal coils of differing radii, carry magnetic flux in opposite directions about their common centerline. According to Maxwell's equation, this produces bucking electric fields along said centerline. Because the two solenoids have different radii, the parallel spring constant of both coils is negative. The negative mass together with the negative spring constant produce a real resonant frequency which can distort the spacetime curvature due to the creation of powerful spikes of negative mass. This phenomenon, similar to the common electrical thunderstorm, opens up a wormhole into hyperspace through which low-density hyperspace energy can enter into our dimension.

Abstract: A propulsion device which takes advantage of the fact that the mass of an object will decrease if the energy density of the object changes rapidly. The energy density is changed by causing rapid mechanical deformations of the object. By these means, the mass of a rotating object is decreased to one side of its axis of rotation, creating an unbalanced centrifugal force that acts on the rotating object as a propulsive force in the direction from the lower mass half toward the higher mass half. The propulsive force is used to propel an object or hold an object in position in opposition to an outside force or provide mechanical energy for a purpose such as the generation of electricity.

Abstract: A craft that includes superconductive materials that are supported within the geomagnetic field of the earth by means of the Meissner effect. The craft is propelled by means of directing a current from a point to another therein which creates a propelling force thereon within such magnetic field as determined by the right-hand motor rule.

Abstract: The cryogenic propulsion module comprises a main cryogenic thruster (10), two attitude-controlling secondary thrusters (21, 22), tanks (31, 32, 33, 34) for feeding cryogenic propellants, a device for intermittently pressurizing the tanks (31, 32, 33, 34), and a device for initiating firing of the main cryogenic thruster (10) in intermittent manner while the tanks (31, 32, 33, 34) are intermittently pressurized. The device for intermittently pressurizing a tank (31, 32, 33, 34) comprises a heat exchange circuit associated with a heat accumulator (61, 62) and a device (71, 72) for putting a predetermined quantity of a propellant into circulation in the heat exchanger circuit. The module also comprises a device for heating the heat accumulator (61, 62) in the periods between two consecutive firings.

Abstract: An aircraft engine includes an exhaust gas purifying device for purifying exhaust gas from the engine, and a switching device for switching the engine between an emission-emphasized mode in which the exhaust gas from the engine is purified by the exhaust gas purifying device and an output-emphasized mode in which emphasis is placed on engine output.

Abstract: A propulsion device which takes advantage of the fact that the mass of an object will decrease if the energy density of the object changes rapidly. The energy density is changed by exposing the object to a rapidly changing electric field or magnetic field or by causing the object to experience quantum mechanical tunneling. By these means, the mass of a rotating object is decreased to one side of the axis of rotation, creating an unbalanced centrifugal force that acts on the rotating object as a propulsive force in the direction from the lower mass half to the higher mass half. The propulsive force is used to propel an object or hold an object in position in opposition to an outside force or provide mechanical energy for a purpose such as the generation of electricity.

Abstract: A take-off device includes a telescopic arrangement of three pipes arranged in a frame. The telescopic arrangement can pivot to a limited extent. The frame is mounted on a horizontal axis running through a center of gravity of the device and a centroidal axis of a lift of an airplane wing, whereby the frame can pivot around the axis. Forces exerted between the telescopic arrangement and the frame are transmitted via a bushing wedged on an outer pipe of the three pipes. A compressed gas accumulator can be opened by means of an actuating pressure signal, whereupon the telescopic arrangement extends outward. A bottom portion of an innermost tube knocks against a fixed point on the ground, which allows the airplane to accelerate to a lift-off speed. After the telescopic arrangement has extended outward, the telescopic arrangement retracts inward using a compressed gas stored in a pressure chamber.

Abstract: Provided is a laser propelled craft having a) a forebody or nose, b) a tapering parabolic afterbody optic or mirror, c) a shroud mounted therebetween and extending aft to define an annular space around a portion of the afterbody near its base and d) means to transmit a pulsed laser beam toward the laser craft and afterbody optic and thence to focus into the annular shroud. The laser beam is pulsed to heat and pressurize the air in the annular space to expand same and propel such craft, the afterbody and shroud being so shaped as to self center or remain in the laser beam as the craft is propelled thereby. Such craft, which is spin-stablized, can also carry a fuel insert ring mounted in the shroud around the afterbody, to be ablated by the laser beam at a desired altitude, so as to transition from an air breathing craft to a rocket craft, when the atmospheric density becomes too low, e.g., at 30 km altitude so that the lasercraft can thereafter be propelled into, e.g., low earth orbit.

Abstract: A microthruster having an inverted exhaust system traps burst diaphragm fragments providing a clean exhaust while an exhaust port provides increased back pressure for efficient combustion of a propellant charge in a fuel cell. A converging diverging micronozzle provides a predictable exhaust vector for improved microthrusting well suited for propulsion system on small spacecraft.

Abstract: A lift and propulsion device is presented which utilizes Bournelli's Principle and the principle of relative motion to create lift. A series of discs are arranged in coaxial alignment. Each successive disc rotates in a direction opposite from the direction of rotation of the disc above it. Air is introduced at the lower outer circumferential surface of the first disc. The introduction of air at this point, as well as the relative motion of the counter-rotating surfaces between the first and second discs creates a large amount of lift. Air is introduced onto the opposite outer circumferential lower surface of the second disc, in the direction of rotation of the second disc. The introduction of this air creates a large amount of lift between Discs B and C. Each successive disc rotates in an opposite direction from the disc above it and has air interjected onto the lower circumferential surface of that disc in the direction of rotation of the disc.

Abstract: A lift-providing unit including two weight units disposed at opposite ends of a rotating armature, at least one of the weight units being capable of generating a recoil force. Lift is provided by the recoil force multiplied by the centripetal force of the rotating armature.

Abstract: A compound exhaust system including two or more stages, preferably three, uses the force of exhaust gases traveling from a thrust generating source through the exhaust system to maximize thrust and minimize wasted energy consumption. In particular, the compound exhaust system for a thrust generating source comprises at least a first stage exhaust and a smaller, second stage exhaust. Various reflections of high speed traveling gases are provided and the resultant pressures induced during this travel supplement the thrust provided by the thrust generating source, which can be a jet engine. The invention also relates to a novel airframe that uses multiple engines having the inventive compound exhaust system.

Abstract: An airborne remote piloted vehicle does not require onboard fuel to greatly extend its endurance and payload capability. Photovoltaic cells are provided on substantially the entire bottom surface of the RPV to receive high intensity radiation beamed up from a ground station. The photovoltaic cells can be made responsive to visible light, infrared light and/or ultraviolet light emitted from lasers that direct narrow, high energy beams, or other directable narrow beams of other wavelengths of high energy radiation, including but not limited to microwaves. The cells convert the beamed up radiation to power at least one electrical motor driven propeller and instrumentation for onboard components including sensors, lasers, radio transmitters, and associated instrumentations. Control signals may also be beamed up or otherwise transmitted to the vehicle to control its transport to and hovering at an on-station location and to activate the onboard components for reconnaissance, monitoring, and relaying data.

Abstract: Mach's principle and local Lorentz-invariance together yield the prediction of transient rest mass fluctuations in accelerated objects. These restmass fluctuations, in both principle and practice, can be quite large and, in principle at least, negative. They suggest that exotic space time transport devices may be feasible, the least exotic being “impulse engines”, devices that can produce accelerations without ejecting any material exhaust. Such “impulse engines” rely on inducing transient mass fluctuations in conventional electrical circuit components and combining them with a mechanically coupled pulsed thrust to produce propulsive forces without the ejection of any propellant. The invention comprises a method of producing propellant-less thrust by using force transducers (piezoelectric devices or their magnetic equivalents) attached to resonant mechanical structures.

Abstract: In an air intake structure (14) of an aircraft engine pod, the link or connection between the air intake lip (15), the front reinforcing frame (16) and the acoustic panel (17) is implemented in such a way that the lip (15) can be dismantled without breaking the link between the frame (16) and the panel (17). Moreover, the internal, rear part (15a) of the lip (15) normally covers the front part (17a) of the panel (17), as well as the members (22, 24) ensuring the link between the latter and the frame (16).

Abstract: A traveling-field, magnetic propulsion system and operating method is provided for achieving economical space travel. The system is based upon designing the vehicle in the form of a single-stage streamlined circular toroidal airfoil containing a thin-walled superconducting solenoid. It is initially launched vertically off the earth's surface into a vacuum environment at 125 km using conventional rocket propulsion. It is then accelerated along a high-inclination trajectory by a traveling repulsive magnetic field generated by ejecting an easily ionizable low-density gas cloud in the vehicle's magnetic field and transmitting a high-power, plane-polarized, microwave beam at the cloud tuned to the electron cyclotron resonant frequency. The transmitter is constructed horizontally on the earth's surface as an electronically-steered, phased array several hundred meters in diameter energized by a large superconducting energy storage system.

Abstract: A propulsion system for aerospace vehicles employs dipole radiators in an interlayer space between outer and inner layers of the vehicle hull. Microwaves are applied, via a control console, to the radiators. The hull may be configured as sectors, and energy may be applied sector by sector to control levitation and propulsion. The outer hull layer can have a grooved inner surface, and may be formed of a titanium or beryllium alloy.

Abstract: Mach's principle and local Lorentz-invariance together yield the prediction of transient rest mass fluctuations in accelerated objects. These restmass fluctuations, in both principle and practice, can be quite large and, in principle at least, negative. They suggest that exotic space time transport devices may be feasible, the least exotic being "impulse engines", devices that can produce accelerations without ejecting any material exhaust. Such "impulse engines" rely on inducing transient mass fluctuations in conventional electrical circuit components and combining them with a mechanically coupled pulsed thrust to produce propulsive forces without the ejection of any propellant. The invention comprises a method of producing propellant-less thrust by using force transducers (piezoelectric devices or their magnetic equivalents) attached to resonant mechanical structures.