Abstract: A programmable crewmember emergency ejection system is disclosed which will eject the crewmember expeditiously from a disabled aircraft, while at the same time assuring that the crewmember will not be subjected to forces that are beyond crewmember tolerance. This is accomplished by a control system involving sensors having signals that are processed and used to vary ejection thrust and acceleration onset rate. The system involves a two phase ejection: A catapult phase followed by a rocket phase, both phases cooperating to provide a substantially constant maximum thrust that is well within human tolerances such that a second jolt to the crewmember is substantially minimized.

Abstract: An earth orbiting satellite (10) having an interior portion (22) supporting heat generating elements (26) and an exterior portion (12) having a thermal radiator (20) for heat radiated by these elements, is provided with reflectors (34s, 34c) in the annulus between the interior and exterior portions, the reflectors being configured to reflect radiation from the axially extending side surfaces of the heat generating elements to the thermal radiator and to conduct heat from the heat generating elements and radiate the conducted heat to the thermal radiator.

Abstract: A single-stick control system for helicopters, by which at least four different flight control functions of piloting the craft--cyclic, collective with simultaneous engine throttling, independent throttling for one or more engines and including immediate transition to emergency autorotation--may be performed by the manipulation of the single stick by one and the same hand of the pilot.

Abstract: In the operation of modern tactical aircraft, crew members are subjected to periodic high acceleration loads that cause fatigue and a decrease in operating capacity. Restraining the torso of a crew member and pulling the crew member back against the ejection seat (2) of the aircraft would help prevent such fatigue. Known restraint and haul back apparatus for use during ejection are not adapted for repeated in flight use. The invention provides a single mechanism that retracts torso restraint straps (6) any number of times during in flight maneuvering and also retracts straps (6) for ejection. A loop (7) of each strap (6) extends around an inflatable member (28). When in flight acceleration loads exceed a preset limit, engine bleed air inflates member (28) to expand loops (7). This retracts straps (6) and positions the crew member. Member (28) is allowed to deflate when the acceleration subsides. When the ejection procedure is initiated, a gas generator (44) inflates member (28).

Abstract: A pilot arm retention system for an aircraft ejection seat which includes ertia reels and a parachute is comprised of a pair of nets connected between respective sides of the seat and a pair of deployment straps which are releasably coupled to the inertia reel straps and parachute risers and routed down over the front of the seat through a pair of snubbers to fixed points on the cockpit floor.

Abstract: A combination lift and thrust device for increasing the performance of an aircraft by simultaneously reducing drag and augmenting the thrust of a turbojet engine carried within the device. The device comprises a wing of generally airfoil shape having numerous geometrically spaced apertures penetrating its surface, a turbojet engine carried within the wing, an elongated exhaust plenum attached to the turbojet having a number of strategically positioned exhaust nozzles, and a mixing chamber having a forward opening and a rear nozzle also carried within the wing. The mixing chamber forward opening is cooperatively associated with the exhaust nozzles to form an ejector drawing air through the apertures in the wing into the forward opening, mixing the air with the exhaust gases from the turbojet to provide thrust augmentation, and exhausting the air and gas mixture from the rear nozzle of the mixing chamber.

Abstract: The steering or control force for operating a steering column in an aircraft, especially in a rotary wing aircraft, is stabilized. The steering column influences through an articulated steering or control linkage the elevator assembly or the rotor blade adjustment, whereby a signal is employed which is dependent on the measured flight speed. It is necessary to signal to the pilot at all times how the steering column must be moved. Such signalling must be definite and free of any disturbing influences and the pilot must receive such signalling through the steering column manual force which is a force reacting to the operation of the steering column. For this purpose a speed dependent signal is supplied to a servomotor. This signal rises with the flight speed at least above a preselectable threshold value. The servomotor in turn controls the tensioning state of a spring which is pivoted at one end to the steering column and at the other end to the displacement member of the servomotor.

Abstract: Separated laminar flow boundary layers are stabilized by delaying a transition into a turbulent flow and by reducing the size of the laminar boundary layer separation zone downstream of a disturbance in the surface contour of a body in the flow, such as a backward step in the body surface, e.g., where sheet metal layers overlap in the surface of an aircraft wing. This purpose is accomplished by suction inlets in the surface just upstream of the disturbance and blowing outlets just downstream of the disturbance and by a flow channel interconnecting these inlets and outlets. Passage of a portion of the flowing medium through these passages is automatically assured due to a pressure differential between the inlets and outlets.

Abstract: An apparatus for moving aircraft on flat surfaces with the aid of cables which, on the one hand, act on the aircraft and, on the other hand, pass to winch drums via guide pulleys which are in part displaceable is characterized in that, for moving aircraft, in particular helicopters, multi-drum winches are provided on a ship's deck with the winch drums being drivable via differential transmissions by two motors which are controllable by means of a joystick operable in the sense of the intended movement of the aircraft.

Abstract: A kit for converting a motorcycle to an aircraft or airborne vehicle includes a glider type parachute with fore and aft lines for connecting to and supporting a motorcycle, in a balanced position, with a propeller system including counter rotating propellers mounted on a pair of concentric shafts and driven by rollers drivingly engaging the rear drive wheel of the motorcycle. Directional control by means of control lines attached to the rear of teeter bars suspended below the wing and connected by directional control lines to outriggers attached to the front wheel structure of the motorcycle.

Abstract: A fire-extinguishing system for helicopter decks (10) comprises nozzles (24, 25) for the supply of foam or water to the helicopter deck and to a helicopter and the like placed on the helicopter deck. At the outer edge of the helicopter deck, just by a submerged gangway (13), and preferably also across the helicopter deck in or by an associated drainage duct (29), there is permanently arranged a conduit system (21, 22, 23) for foam or water, equipped with a first and a second set of nozzles. A first set of nozzles is adapted to direct a jet of foam or water of relatively low strength and relatively small range towards its respective established region of the helicopter deck in order to squirt or spray the same with foam or water. A second set of nozzles is adapted to direct a jet of foam or water of relatively high strength and relatively long range substantially in a direction towards the center of the helicopter deck.

Abstract: A crashworthy helicopter cockpit having a pyrotechnic system actuated by a stroking pilot seat for repositioning the upper portion of the cyclic control stick upon a severe or crash landing that is independent of aircraft electric and hydraulic systems.

Abstract: A substantially one piece molded shell ejection seat (10) having a rocket motor propulsion system (74), the propulsion system (74) being adapted to be integrated into the molded seat (10) during the molding process. The seat body (12) has upper and lower side walls (14, 16, 20, 22), front wall (60) between the lower side walls (20, 22) and back wall portions (30, 32, 34, 36, 38, 40, 42, 44). A molded backrest panel (50) is removably secured to the body (12) to extend generally between the upper side walls (14, 16). The rocket motor propulsion system (74) is incorporated within the body (12) below the upper side walls (14, 16), within the lower side walls (20, 22), generally rearwardly of and below the backrest panel (50), and generally rearwardly of the occupant sitting area (66). A rocket nozzle (78) is connected to the motor (86) by a manifold (82) and is fitted generally within the lower back seat periphery and seat envelope.

Abstract: A vortex generator mounted to an upper lifting surface of an airfoil, and having an upstanding generally planar vortex generating member. The forward edge portion of the member slants first upwardly and rearwardly from the airfoil surface, and then curves in a continuous convex rearward curve to blend into a substantially horizontal rearwardly extending upper edge portion. This vortex configuration alleviates unwanted secondary vortices.

Abstract: Aerodynamic flow conditions at the air intake of gas turbine engines, espally aircraft engines, comprising boundary layer deflectors are improved by movably arranging the boundary layer deflectors so that they may be retracted flush into the aircraft fuselage during take-off and low speed flight, and may be extended to an operating position during high speed flight. A similar retractable boundary layer deflector may be provided for an air intake for an auxiliary engine, which operates intermittently to drive auxiliary devices of an aircraft. When the auxiliary engine operates the air intake is open and the deflector is extended thereby improving the intake air flow conditions. When the auxiliary engine is shut down, the air intake is covered by a control flap and the deflector is retracted flush into the fuselage.

Abstract: An elevator system for use in a wide-body commercial aircraft having multiple levels within the aircraft provides an elevator shaft that extends through at least two of the levels of the aircraft. The elevator shaft communicates with an opening in the hull of the aircraft. An elevator car is mounted within the shaft and controls and a drive unit are associated with the car to move it within the shaft and also out through the opening in the hull to provide access to and from the aircraft. At least a portion of the car remains in the shaft at all times to provide some lateral stability to the car.

Abstract: A cascaded micro-groove aerodynamic drag reducer is provided by creating a plurality of spaced-apart, microscopic grooves in the aerodynamic surface. Each of the grooves is defined by oppositely disposed side walls with each of the side walls of each groove having at least one catenary shaped surface provided thereon. In the preferred embodiment, each of the side walls is provided with a plurality of catenary shaped surfaces with each of the catenary shaped surfaces having a plurality of smaller catenary surfaces provided thereon.

Abstract: A thermal blast shield (64) is located on an aircraft (10) between two adent seats (20 and 22) to be stored in a housing (62) during normal aircraft operation. The thermal blast shield includes cables (84 and 86) passing through fairleads attached to the aircraft and then connected to the seats to pull the shield out of the housing and fully deploy it as the seat is ejected. A break-away mechanism (100, 102) causes the cables to break/separate after the thermal blast shield is fully deployed and jamming/locking mechanisms (104, 106) further control deployment of the thermal blast shield and preclude its post-deployment retraction. The thermal blast shield can be stowed window-shade like or accordianfold-like, and can be formed of a variety of flexible thermal resistant, blast resistant materials.

Abstract: The difference in dynamic pressure in the propeller slipstreams as measured by sensors 20 and 20a is divided by the freestream dynamic pressure generating a quantity proportional to the differential thrust coefficient. This quantity is used to command an electric trim motor 26 to change the position of trim tab 14 thereby retrimming the airplane to the new asymmetric power condition. The change in position of the trim tab produced by the electric trim motor is summed with the pilot's input to produce the actual trim tab position.

Abstract: System for retaining or releasing a number of panels piled onto a supporting structure, such as solar panels of a spacecraft which can be deployed from the piled condition and retracted. The panels each comprise a number of passages at a distance of the edge defining a number of channels through the piled panels. A retainer extending through each channel, comprises operating elements at one side connected to control means attached to the supporting structure and at the other side connected to one or more seizing elements, which under control of said control means and through said operating elements can be moved from a retaining condition in which they seize the outer panel of the pile to a releasing condition in which they do not obstruct the deployment of the panels.