Abstract: A nozzle failsafe nozzle actuating system for an aircraft gas turbine engine variable exhaust nozzle having a plurality of pivotal flaps circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle is provided with a number of primary actuators which are operably connected to nozzle flaps for pivoting and setting an attitude of the flaps relative to the centerline and wherein each of the primary actuators is extendable between a fully extended position and a fully retracted position, and a failsafe nozzle actuating actuator for setting the attitude of each of the flaps to a failsafe attitude during a failsafe mode of the nozzle actuating system wherein the failsafe attitude is such that each of the primary actuators is at a partially retracted position between the fully extended and the fully retracted positions.

Abstract: A brace for cyclic loads includes a tube having first and second ends and a tube wall and a tube axis. The tube wall defines a plurality of first bores radially arranged about the first and second ends of the tube. The first bores extend through the tube wall along first bore axes that are substantially aligned axially with the tube axis. A first end fitting is removably attached to the first end of the tube at an end of the first end fitting. The end of the first end fitting defines a plurality of second bores that have second bore axes. The plurality of second bores are substantially aligned axially and radially with the plurality of first bores. A second end fitting is removably attached to the second end of the tube at an end of the second end fitting. The end of the second end fitting defines a plurality of third bores having third bore axes. The plurality of third bores are substantially aligned axially and radially with the pluralities of first and second bores.

Abstract: An outer cowl panel (24) for an engine nacelle (20). The outer cowl panel (24) includes integral track fairings (30) at aft side edges of the outer cowl panel. The outer cowl panel (24) also includes a chamfered leading edge having outer face sheets (88A, 88B) that extend over the leading edges of a stepped stack of prepreg sheets (88C, 88D, 88E, 88F).

Abstract: A ram air turbine includes a reaction turbine and an electrical generator that is driven by shaft power of the reaction turbine. A scoop directs a flow of ram air to an inlet of the reaction turbine and creates a pressure head for the reaction turbine. The reaction turbine and the scoop are contained entirely within a pod. The ram air turbine further includes a turbocompressor, including a turbine stage and a compressor stage, which provides a stream of cooled air to equipment inside the pod. The turbocompressor also reacts loads shed by the electrical generator.

Abstract: This relates to a helicopter in which the outlet nozzle from the turbine engine is provided with an exhaust pipe which mixes the combustion gases with fresh air and directs the mixture downward. Viewed from the outside of the helicopter, the exhaust pipe is completely concealed by a cowling which is separated from said exhaust pipe by an empty intermediate space, air intakes being provided to create a flow of ambient air, including during hovering flight, along the intermediate space as far as an outlet which is open substantially vertically downward.

Abstract: A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

Abstract: A fixed geometry duct defining a gas turbine engine exhaust nozzle includes a plurality of circumferentially adjoining flat triangular facets and coaxial first and second openings at opposite ends thereof. A method of making the duct includes scribing a plurality of lines on a flat sheet metal plate to define the facets, and bending the plate at each of the lines to form the duct.

Abstract: A Satellite Weather Modification System (SWMS) uses earth satellites to harness solar energy to modify the thermodynamics and composition of the earth's atmosphere. SWMS has three subsystems: The first subsystem includes a network of earth satellites called Satellite Engines (SEs) used to reflect solar energy and/or transform solar energy into other forms of energy beams discharged at specified locations. The media at these locations and the media through which the energy beams pass absorb these energies and change them into heat. The second subsystem includes a large network of Remote Sensing Devices (RSDs). These sensors are used to measure local media compositions, dynamic parameters and thermodynamic properties. Sensor measurements are fed back to the third subsystem, which includes a network of Ground Control Stations (GCSs). GCSs provide energy beam guidance by estimating each beam's characteristics and its aim point trajectory as functions of time.

Abstract: An exhaust nozzle for a gas turbine engine includes a converging inlet duct disposed in flow communication with a diverging outlet duct at a throat therebetween. An ejection slot is disposed at the throat, and compressed air from the engine is selectively injected through the slot for fluidically varying flow area at the throat for exhaust gases from the engine.

Abstract: An aircraft power plant for vertical take-off and landing comprises a jet propulsion unit having an air inlet and an exhaust outlet and incorporating a combustion chamber, a high pressure compressor for supplying air from the air inlet to the combustion chamber, a fuel inlet for supplying fuel to the combustion chamber, and a turbine coupled to drive the compressor and arranged to be driven by the exhaust gases passing from the combustion chamber to the exhaust outlet. Swivelling front nozzles are provided for selectively directing a proportion of air from a fan arrangement downwardly in front of the propulsion unit and swivelling rear nozzles are provided for selectively directing at least a proportion of the exhaust gases from the exhaust outlet downwardly to the rear of the propulsion unit, in order to effect lift on take-off or landing.

Abstract: An electrical power system for an aircraft includes an ac generator bus, an air conditioning system ("ACS") generator and a main engine generator. The ACS generator supplies primary ac power to the bus while the frequency of the ac power is within a frequency range. If the frequency of the ac power goes outside the frequency range, the main engine generator supplies backup ac power to the bus. The frequency of the ac power generated the ACS generator is maintained between upper and lower limits. Such ac power can be used directly by certain ac loads onboard the aircraft. Other ac loads onboard the aircraft are supplied with fixed frequency ac power by reduced-size inverters.

Abstract: An aircraft engine vibration analysis system is provided with at least one vibration sensor disposed proximate an aircraft engine. The analysis system is further provided with a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine. The analysis module is provided with a multiple pin input port which is connectable to the vibration sensor. The analysis module is further provided with test sequence select circuity which is in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port. The analysis system is further provided with a sensor connecting cable which is connectable to the vibration sensor and the analysis module input port.

Abstract: The bleed air requirements for a pressurization and environmental control system for the cabin (10) of an aircraft may be reduced by a system that includes a turbomachine (20) having a rotary compressor (22) driven by a turbine wheel (26). A ram air inlet (16) is connected to the compressor inlet (28) and the aircraft is provided with a cabin air exhaust port (18) which is connected to the outlet (34) of the turbine wheel (26). A heat exchanger (40) has a cabin inlet air flow path (42) and a cabin outlet air flow path (44) in heat exchange with one another. The cabin inlet air flow path (42) is connected to the outlet (30) of the compressor (22) and to the cabin (10) of the aircraft. The cabin outlet air flow path (44) is connected to the cabin (10) as well as to the inlet (32) of the turbine (26).

Abstract: A fencing assembly (66) for prohibiting circulation of primary and/or fan airflows (52), (54) into a bounded low pressure region of a jet engine installation. The fencing assembly includes one or more flow control fences. In an exemplary application, the fencing assembly includes a number of fences positioned around the sides of a batcave (48) bounded low pressure region that is located between a primary exhaust nozzle (20) and strut fairings (30). The fencing assembly includes five fences, each fence being connected to either the primary exhaust nozzle or the strut fairings. The five fences include single fences (70), (72) positioned along each lateral side of the batcave; two rear fences (74), (74') positioned circumferentially about rear regions of the batcave; and an arcuate fence (76) positioned near the two rear fences to form a half circle. The fences include a foot portion (78) and an upright portion (80).

Abstract: In a turbofan jet engine installation including a low pressure area (48) located between a primary exhaust nozzle (20) and strut fairings (30), an improvement including a fencing assembly (66) for reducing interaction of fan air (52) with air in the low pressure area. The fencing assembly (66) includes two pairs (70), (72) of opposed flow control fences (68) connected to the primary exhaust nozzle (20) at locations laterally outboard of the strut fairings (30). A first pair (70) includes fences formed of a single piece connected directly to the primary nozzle (20). A second pair (72) includes fences formed of a number of longitudinally spaced-apart segments (82). The segments (82) are connected to one face of an elongated attachment strap (84) with the opposite strap face being connected to the nozzle. Each fence includes a foot portion (78) and an upright portion (80) extending outwardly from the foot portion.

Abstract: A centerline mounted overbalanced multiple main jet engine configuration. The multiple jet engines are centerline mounted rather than parallel offset. While each jet engine is a "main" engine, capable of safely operating the aircraft in the event of a failure of the other engines, the engines are overbalanced in the sense that at least one of the main engines has substantially greater thrust than the other main engines. All of the main engines operate at critical periods of flight, but only one or the other of the main engines operates at other periods. The configuration of this invention combines the efficiency and performance of a single engined aircraft with enhanced safety advantages.

Abstract: A special purpose helicopter based on an existing airframe, power train, and engine, modified to provide greatly enhanced performance, payload, speed and maneuverability. The modification consists of modifying an original helicopter universal transmission center case for installation of twin drive shafts, at 180.degree. apart, and mounting a second engine on the airframe structure, at 180.degree. to the first engine, and forward of the transmission. An exhaust system for the second engine is split into two units for directing the exhaust outwardly and upwardly.

Abstract: A variable area exhaust nozzle 26 is provided. The variable area exhaust nozzle 26 includes a nozzle opening 30 and a plurality of nozzle flaps 38 and 40. The nozzle opening 30 has a cylindrical area and a circumference. The plurality of nozzle flaps 38 and 40 are supported about the circumference of the nozzle opening 30. The nozzle flaps 38 and 40 have an axis of rotation 52. The nozzle flaps 38 and 40 are positioned to rotate into the nozzle opening 30 to decrease the cylindrical area of the nozzle opening 30 and to rotate out of the nozzle opening 30 to increase the cylindrical area of the nozzle opening 30. The nozzle flaps 38 and 40 rotate to vary the cylindrical area of the nozzle opening 30 and to reduce the forces required to rotate the nozzle flaps 38 and 40.

Abstract: An aircraft engine has a nozzle shaped to reduce the volume of Mach diamonds being formed in the exhaust plume. A notch or recess is formed in the discharge edge of the nozzle. The recess provides a forward discharge edge that causes additional Mach diamonds to occur at a regular spacing from the forward discharge edge. These additional Mach diamonds are axially staggered with other Mach diamonds, which occur at regular spacing from the rearward edge of the nozzle discharge edge. Each Mach diamond has a volume that is substantially less than one-half the volume of a Mach diamond created by a conventional nozzle. This results in less high temperature areas per axial increment in the plume than the prior art exhaust plumes. Because Mach diamonds are the primary cause of high infrared emissions, as well as acoustic noise, a reduction in the total volume of Mach diamonds in the exhaust plume thus reduces infrared emissions, as well as the noise.

Abstract: An aircraft comprises at least one jet engine having a surrounding, open-ended duct coaxial with the engine and spaced therefrom radially to define a passage of annular cross-section. The casing or duct extends upstream and downstream of the jet engine and tapers internally in the forward direction over a region, in which a leading edge of a casing of the jet engine is disposed. Upstream of the tapering region, the interior of the duct forms a cylindrical entry section of the passage through the duct, in which an axially displayable open-ended tube is disposed, spaced radially from the wall of the entry section of the duct passage.

Abstract: A nacelle apparatus for an airplane of the type having nacelles for jet engines suspended under a wing via pylons includes lip-shaped small wings corresponding to the nacelles for the jet engines. Each lip-shaped small wing extends from the upper trailing edge of each nacelle to the opposite sides of a pylon. The nacelle apparatus assures that lift/drag properties of the nacelle apparatus can be improved by reducing a magnitude of drag induced by aerodynamic interference of the main wing with the nacelle.

Abstract: In a helicopter having a main rotor, a tail boom and a circulation control slot along one side of the tail boom, and a thruster which is selectively directable at either side or both sides of the rear end of the tail boom, anti-torque and yaw control are effected by generating separate air flow streams of different pressures by means of separate pressure means and conducting said separate air flow streams at said different pressures in separate passages to respectively the circulation control slot and to the thruster.

Abstract: A ducted fan turbine engine includes a nacelle and an outer discharge nozzle mounted on an aircraft wing by a pylon. The nacelle includes to parts which are hinged to the pylon for pivoting movement between an open position and a closed, operational position. Each nacelle part contains a bypass air duct. Spaced spigot locators and blade locators are positioned at the forward edge of the discharge nozzle and spigots and blades are correspondingly located round the rear edge of the nacelle parts. The locators and their corresponding spigots and blades are arranged so that on closure of the nacelle parts they engage one another and transmit the flight loads through the nacelle.

Abstract: Indexing a propeller blade so it leads intake valve timing by a specific amount causes an increase in engine power. The proper indexing allows the high energy propeller wake in the form of an acoustic wave to be ingested by the induction system and arrive at the intake valve just as the valve is opening. When the Wave arrives just as the valve is opening, the wave causes a momentary increase in manifold pressure which adds pumping potential to force additional airflow into the engine cylinders which results in a power increase. This technique called propeller syncro-phasing causes the propeller blade to behave as a "zero stage supercharger". Adding a trailing edge extension to the propeller blade chord at the radius corresponding to the induction inlet causes a local increase in slipstream total energy adding additional energy to the induction airflow resulting in additional engine power.

Abstract: An active noise control subassembly for reducing noise caused by a source (such as an aircraft engine) independent of the subassembly. A noise radiating panel is bendably vibratable to generate a panel noise canceling at least a portion of the source noise. A piezoceramic actuator plate is connected to the panel. A front plate is spaced apart from the panel and the first plate, is positioned generally between the source noise and the panel, and has a sound exit port. A first pair of spaced-apart side walls each generally abut the panel and the front plate so as to generally enclose a front cavity to define a resonator.

Abstract: An active noise control subassembly for an aircraft engine. An aircraft engine noise radiating panel is bendably vibratable to generate a canceling noise generally opposite in phase to at least a portion of the discrete tonal noise produced by the engine. A piezoceramic actuator plate is vibratable by an applied electric AC signal. The plate is connected to the panel such that vibrations in the plate cause bending vibrations in the panel and such that the plate is compressively prestressed along the panel when the panel is free of bending vibrations. The compressive prestressing increases the amplitude of the canceling noise before the critical tensile stress level of the plate is reached. Preferably, a positive electric DC bias is also applied to the plate in its poling direction to increase the amplitude of the canceling noise before the sum of the AC signal and DC bias exceeds the depolarization voltage in a direction opposite to the poling direction.

Abstract: A floating speed electrically driven suction system for sucking boundary layer air flow off the external surface of an aircraft. A variable speed electrical generator drives a variable speed electrical motor which in turn drives a variable speed pneumatic compressor. Inlet guide vanes are automatically adjustable to compensate for variations in pressure. A surge control valve is operable to port in additional inlet flow as needed to avoid low volumetric surge in the suction compressor.

Abstract: A system for protecting the strut and wing structure of an airplane from high temperatures proximate the exhaust nozzle end of a jet engine employs a set of outer spring metal fingers attached to the exhaust nozzle outer sleeve and which bear against the strut structure, and a second set of inner spring metal fingers, interleaved with the first, which close off interfinger slots in the first or outer set whereby to maintain firewall integrity. Hot gases are thereby prevented from passing forwardly into the strut structure and wing area so as to protect the same in the event of an engine fire.

Abstract: A novel, high-altitude, solar powered aircraft, capable of staying aloft at high altitudes for many months or even years to conduct around the clock surveillance and/or reconnaisance, includes a forward wing with solar energy capturing cells, a rear wing, inflated pontoons for keeping the aircraft aloft, suspension wires attached to the pontoons, a gondola suspended from and connected to the wires, control apparatus for moving the gondola along the wires, shifting the weight of the aircraft and thereby enabling banking to optimize exposure of the solar cells to the rays of the sun. The gondola preferably contains a sensor suite, power generating and storage apparatus, and synthetic aperture radar imaging apparatus.

Abstract: The invention is a shroud for a reversible thrust fan, the shroud having a inlet duct and an exhaust nozzle with the fan located there between. In general terms, the shroud includes a system for increasing the efficiency of the exhaust nozzle when acting as an inlet duct when the fan is providing reverse thrust. The system comprising a plurality of auxiliary inlet duct systems spaced about the circumference of the exhaust nozzle in proximity to the rear end thereof, the auxiliary inlet duct systems extending from the exterior surface of the exhaust nozzle to the interior surface thereof. The auxiliary inlet duct systems are movable from a closed position to an open position wherein air can be drawn from the exterior surface of the exhaust nozzle to the interior thereof when the fan is providing reversed thrust.

Abstract: A flade exhaust nozzle for a high thrust jet engine is configured to form an acoustic shield around the core engine exhaust flowstream while supplementing engine thrust during all flight conditions, particularly during takeoff. The flade airflow is converted from an annular 360.degree. flowstream to an arcuate flowstream extending around the lower half of the core engine exhaust flowstream so as to suppress exhaust noise directed at the surrounding community.

Abstract: An isolator assembly for use in minimizing mechanical thermal and/or vibrationary strains between two structures is disclosed. The isolator assebly generally includes two spaced base members which are interconnected by a plurality of equally spaced rods. The length, diameter and material of the rods are determined based on the particular environment within which the isolator assembly is utilized. The invention has particular application in supporting a hot air blower tube within a cowling of a jet engine unit.

Abstract: A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body in substantially a nose down attitude. The system includes an inflatable bag which is stowed on a portion of a flat annular rim of the aft skirt of the booster. The bag is hinged at opposing sides and is provided with springs that urge the bag open. The bag is latched in a stowed position during launch and prior to landing for recovery is unlatched to permit the bag to be urged open and into sealing engagement with the rim. A source of pressurized gas further inflates the bag and urges it into sealing engagement with the rim of the skirt where it is locked into position. The gas provides a positive pressure upon the interior of the bag to preclude entry of salt water into the skirt and into contact with the engine. A flotation arrangement may assist in precluding the skirt of the booster from becoming submerged.

Abstract: An aircraft engine two-dimensional inlet system of the present invention provides a telescoping two-dimensional centerbody that is referred to as a wedge. The telescoping wedge may be of a fixed wedge angle design or a variable wedge angle design. The present invention contemplates single and multi-wedge angle designs of the fixed or variable intermediate wedge angle types having more than one ramp angle. The telescoping wedge has at least one upper and lower pair of longitudinally adjacent wedge forward and aft walls that overlap to form an aft facing step and are in controlled sliding engagement.

Abstract: The present invention relates to a method and apparatus for providing an operable divergent/convergent variable geometry exhaust nozzle for jet propelled aircraft. A multiplicity of hinged, overlapping, nozzle blades circumferentially surround the exhaust nozzle thereby providing a divergent cylindrical exhaust nozzle that may be convergingly reduced to a conical configuration by action of a remotely controlled solenoid.

Abstract: A mixture of urea, ammonia, and water is injected into the exhaust of jet engines to lower the amount of NO.sub.x emitted from jet engines.

Abstract: A control system for hydraulically controlling variable engine structures is disclosed in which the control system utilizes hydraulic fluid identical to that used by the aircraft hydraulic control circuit. A high pressure hydraulic pump, driven by the aircraft engine, may be interconnected with the aircraft hydraulic control circuit, or may be associated with a separate fluid reservoir, to supply pressurized hydraulic fluid to the actuators for controlling the variable engine structures. The engine control circuit also includes a hydraulic pressure modulator to modulate the pressure of the fluid supplied to the actuator and a selector connected between the high pressure pump and, the modulator and the aircraft control circuit to selectively supply the high pressure hydraulic fluid from the pump to either the engine control circuit, or to the aircraft control circuit.

Abstract: An aircraft having a turbojet engine disposed within its fuselage wherein towards the rear end thereof it is provided with a sealing assembly between the rear end of the fuselage and the outer flaps of the nozzle of the turbojet engine, the sealing assembly including a central carrier ring, preferably made of a carbon-epoxy material, secured to the turbojet engine by supporting legs, a hollow front seal at the front end of the carrier ring engaging the inner surface of the fuselage, and a hollow rear seal at the rear end of the carrier ring engaging each of the outer flaps, the carrier ring also engaging the inner surface of the fuselage at a position spaced rearwardly from the front seal.

Abstract: The present invention relates to a method and apparatus for providing an operable variable geometry exhaust nozzle for scale model jet aircraft. A multiplicity of hinged, overlapping, nozzle blades circumferentially surround the exhaust nozzle thereby providing a divergent cylindrical exhaust nozzle that may be convergingly reduced to a conical configuration by action of a remotely controlled solenoid.

Abstract: An electrically powered engine has a tip-driven fan assembly. The engine includes an electric motor which comprise a rotor mounted on the periphery of the fan assembly and a stator mounted to the frame. Power is supplied to the electric motor by a metal/air battery assembly mounted to the frame and having a cylindrical shape. The fan assembly produces a flow of air with at least a portion of the battery assembly. The battery assembly comprises a plurality of metal/air battery cells each having a cylindrical anode, a cylindrical cathode with insulating spacers forming an annular chamber for holding the battery electrolyte.

Abstract: A propelling system for an aircraft having a fuselage and a pair of swept wings, is provided and consists of a pair of propeller driving engines, each carried on top rearward edge of each swept wing so as to push the aircraft forward, a pair of pylons, each carried on bottom of a forward edge of each swept wing and a pair of jet engines, each affixed to a bottom end of each pylon so as to pull the aircraft forward.

Abstract: An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies within said body for effecting a vertical lifting air stream through said assemblies. Power generating devices and devices for coupling the power generating devices to the turbo-blade assemblies for maintaining them in rotary motion. It also includes thrusting devices coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices including a plurality of combustion chambers located below the turbo-blade assemblies for boosting said vertical lifting airstream.

Abstract: An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with an apparatus to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft's wing to reduce its surface drag.

Abstract: An environmental control system for supplying aircraft or cabin air to an aircraft is provided with a propulsive engine compressor bleed supply means and an ECS bleed air flow control means which includes an energy recovery means for using the unrequired or unused energy to pump boundary layer air from the surface of the aircraft, such as from the engine nacelle, and exhaust this air rearward of the engine to produce thrust, thus returning some of this unused energy to the propulsive engine.

Abstract: The invention is a propellant utilization system for flight vehicles operating in both the subsonic and supersonic speed ranges. In particular, the invention uses steam and water produced in the system to replace hydrogen as a coolant and for power generation. It also provides for the utilization or oxygen obtained from air captured by the air inlet instead of oxygen stored in the vehicle.

Abstract: An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with an apparatus to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft's wing to reduce its surface drag.

Abstract: An aircraft propulsion system includes a propeller for propelling the aircraft, an electric motor for driving the propeller, and an electrochemical fuel cell for receiving an oxidizer and providing propulsion power to the electric motor. An air liquefaction system is used for receiving ambient air and providing oxidizer to the fuel cell. Preferably, at low altitude, the air liquefaction system provides oxidizer to the fuel cell and to an oxidizer fuel tank. Then, during high altitude excursions, the oxidizer is provided to the fuel cell from the oxidizer fuel tank. When the oxidizer tank is empty, the aircraft returns to a lower altitude where extraction of oxidizer from the atmosphere is resumed.

Abstract: A breather outlet for the gearbox of an aircraft mounted gas turbine engine comprises an aerodynamic mast which extends from the engine nacelle. The mast contains a breather duct which interconnects the interior of the gearbox with an exhaust outlet. The exhaust outlet is generally rearwardly facing and is spaced apart from the engine nacelle so as to avoid oil staining of the nacelle.

Abstract: A method of operating a scramjet engine having an improved low pressure combustion cycle is disclosed. Apparatus for carrying out the method is also disclosed. The method includes the steps of providing supersonic compressed airflow to a combustor and supplying fuel to the combustor for generating a fuel/air mixture having a predetermined temperature less than a temperature required for spontaneous ignition of the fuel/air mixture. The method also includes igniting the fuel/air mixture for sustaining recombination reactions of the fuel/air mixture for generating combustion gases. In the preferred embodiment, the fuel/air mixture is ignited by generating a boundary layer of airflow having atomic oxygen and channeling the boundary layer into the combustor for mixing with a portion of the fuel for generating a boundary layer fuel/oxygen mixture subject to spontaneous ignition.

Abstract: An electromagnetic ramjet propulsion system is provided for accelerating high mass payloads through the upper atomsphere at orbital velocities. The propulsion system comprises a plurality of coplaner self-supporting superconducting dipole coils several hundred meters in diameter that is initially accelerated to high altitude and supersonic speed by magnetic repulsive forces generated by a plurality of superconducting field coils several kilometers in diameter embeded beneath the earth's surface. The ramjet is accelerated to orbital velocities by a multigigawatt microwave beam that is transmitted from the earth's surface. A reflecting grid of conducting wires is mounted inside the inner dipole which shock ionizes the low dentisy atmospheric gas passing through it.