Abstract: A cooling device for an aircraft turboshaft engine includes a boundary layer suction device formed by a perforated external wall portion of the aircraft, a collector on the inside of the wall portion for receiving the air flowing in through the perforations, and a discharge device discharging the air from the collector. The cooling device is completed by a heat exchanger which is disposed in the path of the air flow through the collector, a pump for pumping fluid to be cooled through the heat exchanger from a circuit of the engine, and a regulator regulating the fluid flow through the exchanger to control the temperature of the fluid. The fluid which is cooled may be from the lubrication circuit, the fuel circuit, or an air circuit of the engine, and the boundary layer suction device is preferably disposed in the pod of the engine.

Abstract: Apparatus and method for performing satellite proximity operations such as inspection recovery and life extension of a target satellite through operation of a "Satellite Inspection Recovery and Extension" (SIRE) spacecraft which can be operated in the following modes (teleoperated, automatic, and autonomous). The SIRE concept further consists of those methods and techniques used to perform certain (on-orbit) operations including, but not limited to, the inspection, servicing, recovery, and lifetime extension of satellites, spacecraft, space systems, space platforms, and other vehicles and objects in space, collectively defined as "target satellites." The three basic types of SIRE proximity missions are defined as "Lifetime Extension", "Recovery", and "Utility." A remote cockpit system is provide to permit human control of the SIRE spacecraft during proximity operations.

Abstract: The life of a target satellite is modified, i.e., extended or terminated by docking an extension spacecraft with the target satellite to form a docked satellite-spacecraft combination. The extension spacecraft is docked with and mechanically connected to the target satellite and includes guidance, navigation, and control systems for performing the rendezvous and docking maneuvers and for controlling the position of the docked spacecraft-satellite combination. The extension spacecraft also includes an onboard propellant supply for accomplishing the rendezvous and docking of the spacecraft with the satellite and for controlling the position of the docked spacecraft-satellite combination. A remote cockpit system is provided to permit human control of the extension spacecraft during proximity operations.

Abstract: An expandable section (12) is provided for an aircraft (10) which includes a movable rigid aircraft section (18) which is attached to the fixed aircraft structure (16) by an elastomeric transition section (14) which permits the movable aircraft section (18) to move between a retracted configuration and an expanded configuration to increase the volume of a cavity within the aircraft. The elastomeric transition section includes elastomeric material (20) having a plurality of holes (22) therethrough. Flexible rods (28, 32) are secured either to the aircraft structure (38) or the movable aircraft section (18) and extend through the holes to permit the elastomeric transition section to expand, contract and bend as necessary to accommodate the movement of the movable aircraft section (18). In one application, the movable aircraft section (18) can form the doors (40, 42) of a weapons bay.

Abstract: A low-cost, liquid-propellant rocket launch vehicle having a central pod that carries an optional final-stage rocket engine cluster, and having additional engine clusters arranged in diametrically opposed pairs of clusters. The pairs of clusters are burned and separated in a staging sequence until the final stage is reached. In the presently preferred embodiment, there are three pairs of engine clusters arranged in a hexagonal configuration about the central pod and each engine cluster contains seven identical engines. The engines are made from light-weight, low-cost materials, without gimbals or other moving parts. Steering of the vehicle is effected by differential control of the engine thrusts of selected engines, using duty-cycle modulation of a plurality of on/off propellant supply valves and, additionally, control of other on/off valves controlling the supply of an inert cryogenic fluid to secondary injection ports on the engine.

Abstract: An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is disclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and compensating gyroscopic moments are then generated and summed with commanded pitch and roll accelerations. Flapping angle phase lags of the rotor blade swashplate are added to the summed signals to cancel any flapping angle phase leads, caused by changes in aircraft or rotor blade speed caused by installation configurations of the rotor blade swashplate.

Abstract: A highly efficient flame arrester adapted for use in preventing an external flame from backflashing upstream in a pipe, or a conduit, or a stream carrying a flammable substance. The flame arrester comprises a contained layer of nested spheroids formed from expanded metal sheets made from magnesium alloy foil. The arrester is useful in fuel tanks, combustion systems, sea-going tankers, hot water or space heaters, and the like.

Abstract: A highly effective module for preventing corrosion of oil well pipes and equipment and for preventing resulting fires and explosions. The module is a collar formed from slitted and expanded metal net and is adapted to fit in the annular space between the oil production pipe and the outer casing of the oil well, to prevent oxygen from the atmosphere from entering the annular space at the top of the well, and to exclude hydrocarbon vapors from the subterranean production zone from entering the annular space at the bottom of the well. The invention also relates to methods for extinguishing a burning oil well.

Abstract: The invention relates to a system for removing the heat that is incident upon an aircraft, and especially a supersonic aircraft, during flight. The incident heat is generated by the constant heating effect of aerodynamic friction on the outer skin of the fuselage, by compression heating at the ram or stagnation point and stagnation edges of the aircraft fuselage, and by the heating of external air as it is compressed to cabin pressure. In the present system, the used cabin air is exhausted out of the cabin through a space between the cabin interior panels and the fuselage outer skin, where the airflow absorbs the heat incident through the outer skin and is heated to approximately the temperature of the outer skin. Next, the heated airflow is preferably first filtered through a filter and is then expanded and cooled through an expansion turbine. The output shaft of the turbine can drive a generator to recover useful electrical energy.

Abstract: A fire retardant delivery system for delivering fire retardant onto a fire. The system 10 includes an aircraft comprises a fire retardant storage and ejection system, and a stabilized three axis gimbal system for providing signals indicative of angle and angle rates of a gimbal with respect to an axis of the aircraft. An infrared sensor system is disposed on stabilized three axis gimbal system. A display is coupled to infrared sensor system for displaying an image produced thereby to a pilot of the aircraft. Aircraft sensors are provide signals indicative of the velocity, altitude, and dive angle of the aircraft. A computer is coupled to the infrared sensor system, to the aircraft sensors, and to the fire retardant storage and ejection system, for computing distance between the aircraft and a hot spot in the fire and for computing an optimal release point for ejecting fire retardant from the aircraft onto the fire.

Abstract: An easily-attachable supplemental wheel apparatus that allows one person to perform the ground-handling functions necessary to maneuver an aircraft or helicopter having a skid configured landing gear. The apparatus includes an axle extending across the landing skids having a pair of spaced eyelets attached to the axle in such a position that one of the landing skids can easily slide through each eyelet. The apparatus includes a pair of wheels rotatably attached to the axle to allow for easy ground movement along with an attachment for securing the axle to the airframe.

Abstract: A method is provided for improving the localization of a robot autonomous mobile unit. A slippage is predicted along a path that the unit is to traverse may be predicted, in that a simplified absolute path trajectory is determined, and based on the unit geometry and motion behavior of three-wheel kinematics, an imaginary slippage derives in the end position. This imaginary slippage can be calculated for various end positions and the most beneficial travel path can thus be selected from a starting point.

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: The invention provides a modular system including one or more interchangeable pressurizable body sections, a front end cap and a rear end cap. A tendon array assembly is coupled between the front endcap and the rear endcap. The body sections are preferably coupled together by a flexible seal. The interchangeable pressurizable body sections may be preloaded prior to launch or left vacant for cargo retrieval from an orbiting facility. Once loaded, the various elements of the modular system may be easily assembled with other elements into a plurality of configurations. The modular system can be attached to an orbiting space structure or utilized within the cargo bay of the NSTS Orbiter to provide a wide range of mission objectives.

Abstract: The apparatus stabilizes loads beneath helicopters to prevent undesirable load movement while allowing in-flight optimization of the load's center of gravity to reduce drag and increase banking capability and top speed. An anchoring bracket secures the apparatus to the helicopter. The apparatus comprises an upper section that controls load pitch and lateral movement and a lower section that controls load height during unloading. A pitch regulator comprises a c-shaped yoke with upper and lower collars penetrated by a hollow shaft and elevator. A lateral movement regulator comprises a coupling and a y-shaped chassis. The coupling comprises a central sleeve captivated between the upper and lower collars and a motor permitting selective rotation about the elevator. The chassis secures to the coupling via a ball and socket and a middle suspension system captivated between coupling and suspension plates. Spaced apart terminal chassis arms support the load via a bearing wing.

Abstract: An elliptical orbit satellite system which describes communication and TT&C with ground stations. Earth stations are located for the circular orbiting satellite in a way such that the line of sight can never include geo synchronous satellites. The ground stations for the elliptically orbiting satellites monitor the position of the satellite, and no antenna communicates with a satellite which is in direct line of sight between the antenna and a geo satellite. Another aspect of the invention locates two TT&C stations, separated in longitude by 90.degree. and configures these stations such that each satellite in each constellation will be able to communicate with one of the two TT&C stations once during each satellite rotation period.

Abstract: A selectively tiltable patient loading system and transport device adapted for use in aircraft is disclosed. The device generally comprises a base assembly interconnected to the floor of an aircraft, a platform assembly capable of receiving and supporting a litter with a patient thereon, and an interconnecting assembly interposed between the base assembly and platform assembly for supportably interconnecting the platform assembly to the base assembly and for selectively tilting the platform assembly relative to the base assembly.

Abstract: A disconnect assembly which is positioned between respective sections of the torque bar for control column controls and permits alternative connection or disconnection of the sections of the control torque bar. This disconnect structure can be included on any or all of the control column torque bars for operating any of the control surfaces of the aircraft.The torque tube disconnect assembly includes a lever rotatably attached to one side of the first torque tube section which has a pair of recesses and a central recess for receiving a pin mounted on a swivel bar. The opposite end of the swivel bar has an interconnect apparatus for engaging the end of the second torque tube section immediately adjacent the first torque tube section. The swivel bar has a pair of arms on either side thereof each of which rotatably supports a separate articulated link for each such arm. The opposite end of each such link is attached to an axle on a mount fixedly attached to said first torque tube section.

Abstract: The present invention is de-icing system that uses electromagnetic actuators mounted within the airfoil of an aircraft to effect de-icing. Advantageously, the actuators have low voltage and current requirements. Each actuator includes conductive strips fabricated on a flexible dielectric sheet. The conductive strips are wound into coils with the actuator shaped into a flattened elongated tube. The axis of the winding coils is coincident with the longitudinal axis of the elongated tube.

Abstract: A linkage arrangement (20) joins a nacelle (12) enclosing a gas turbine engine (10) and a pylon (18) suspended from an aircraft wing. The linkage arrangement (20) counteracts the deflections of the nacelle (12) with respect to the free air stream due to the aerodynamic load. The linkage arrangement (20) includes a plurality of links (22, 24, 32, 34) that substantially duplicate the motion of a four bar linkage mechanism.