Abstract: A system for augmenting yaw control in an aircraft is described which comprises first and second thrust nozzles disposed on the upper surface of the aircraft forebody aft of the forebody nose apex a distance of about 0.5 times the forebody diameter at about 45.degree. to either side of the symmetry plane of the forebody, each thrust nozzle oriented to direct a fluid jet at an angle of about 10.degree. from the surface of the forebody and generally rearwardly toward the symmetry plane at about 60.degree. .+-.10.degree. to the symmetry plane, and a source of pressurized fluid operatively connected to the thrust nozzles for generating the jets.

Abstract: The invention relates to raisable landing gear including a shock absorber having a strut and a sliding rod, together with a two-alignment hinged side-brace. According to the invention, unlocking means are provided to break the secondary alignment, thereby breaking the main alignment while the landing gear is being raised, said means being essentially constituted by a lever mounted to rotate on one of the arms of the main alignment, and by a motor and gear box assembly for driving said rotary lever in rotation and further including an unlocking arm that, when said motor and gear box assembly is in action, co-operates with the lower arm of the secondary alignment to break said secondary alignment. Return means are also associated with the rotary lever to ensure that it returns to its initial position when the landing gear is raised.

Abstract: A helicopter engine fuel control anticipates changes in main rotor torque in response to lateral cyclic pitch commands, to thereby minimize engine and main rotor speed droop and overspeed during left and right roll maneuvers. A fuel compensation signal (100,101) is summed with a helicopter fuel control (52) fuel command signal (67) in response both to a lateral cyclic pitch command signal (LCP) (107) from a pilot operated cyclic pitch control exceeding a left or right threshold magnitude (201,210) and a total lateral cyclic pitch command signal (TCP) (108) from a lateral cyclic pitch control system exceeding a left or right threshold magnitude (202,207,215,220). The magnitude of the fuel compensation signal is dependant upon the direction of TCP and LCP, e.g., left or right, and helicopter roll acceleration (115). Alternatively, the magnitude and duration of the fuel compensation signal is dependant upon the rate of change in commanded lateral cyclic pitch (107,400,407).

Abstract: A portable, temporarily installable and removable safety seat for the carriage of an infant or small child aboard an aircraft includes securing anchors which cooperate with the standard seat or cargo tiedown tracks of most passenger aircraft. The anchors permit the safety seat to be secured directly to the floor of the aircraft in the same manner as other standard seats or other articles. The safety seat may be made foldable or so the back may be removed from the bottom for more compact storage, and may be constructed of relatively sturdy but lightweight materials such as aircraft grade steel tubing or aluminum tubing. Preferably, all of the materials used in the safety seat will meet or exceed the appropriate standards for fire resistance.

Abstract: A helicopter engine fuel control anticipates sudden changes in engine power demand during yaw inputs to thereby minimize engine and main rotor speed droop and overspeed during yaw maneuvers. The rate (121,123) of yaw control (107) position change generates (110) a yaw component (104) of a helicopter fuel control (52) fuel command signal (70). The magnitude of the yaw component is also dependant upon the rate of yaw control position change (703). The fuel command signal yaw component (104) is overridden (113,115) when rotor decay rate (209,217) has been arrested during a sharp left hover turn (216); when the yaw component is removing fuel (239) during rotor droop (238); and when the yaw component is adding fuel (228) during rotor overspeed (227).

Abstract: A pilot's ejection seat is propelled in an upward direction after ejection by employing a high gain signal from a radio altimeter on board an aircraft. The vertically downward high gain vector is inverted by adding 180.degree. to its phase component and providing the resultant signal to an inexpensive gyro or assembly of gyros installed in the seat. The gyros are constantly updated with information concerning the upward vertical direction and upon ejection, the gyros maintain this information for a sufficient period of time to control the ejection seat propulsion system in a manner achieving a vertically upward trajectory that will enable the pilot to clear a disabled aircraft and achieve the orientation necessary to deploy a parachute.

Abstract: A stretcher which is adapted to be hingedly attached to the inside surface of a transportation means is disclosed. The stretcher is provided with orifices through the top and bottom surfaces of the stretcher such that the location of the orifices corresponds to the arrangement of the windows in the transportation means so that the passenger's view is not blocked by the stretcher when the stretcher is not in use.

Abstract: A device for protecting a helicopter and its occupants from damage during a crash or difficult landing. The device includes an inflatable bag attached to the bottom fuselage which covers a totality of the surface of the helicopter's bottom fuselage. The bag is inflatable into a trapezoidal shape having a very large volume, exceeding the helicopter's internal volume, for substantially cushioning the helicopter upon impact with the ground during a crash. The bag is equipped with distortion-control reinforcements for preventing toppling of the helicopter after a landing and bag air-pressure controlling and limiting devices.

Abstract: A hard, semi-rigid cover for protecting vehicle surfaces from damage by esure to the elements or chemical warfare agents is disclosed. A typical surface to be protected by a cover of the invention is a helicopter transparent canopy. Key features of the invention are a seal that forms around the cover perimeter where it fits snugly against the vehicle's outer surface and an air gap that exists between the inside surface of the cover and the vehicle's exterior surface. The cover is made of a moldable polymer material.

Abstract: An unpowered reusable flying wing glider employed in conjunction with an aerodynamically shaped spacecraft without wings so as to permit existing airfield launch and ascent to orbit for a rocket engine takeoff thrust to vehicle weight ratio of less than 1. After an optimum climb angle is established and before wing weight and wing drag degrade performance, the wing is released for a glide return to the launch site. The flying wing zero stage would contain tank(s) for fuel or fuel and oxidizer so that at wing release, the spacecraft tanks are full or nearly full for the continuing trajectory to orbit.

Abstract: An environmentally-sealed parachute deployment system for bail-out parachutes comprising a spring-loaded pilot parachute, an environmentally sealed vacuum bag, a deployment bag having one or two elastic closure loops, and a man-rated parachute. The drag force exerted by the pilot parachute tears open the environmentally sealed bag, initiating deployment of the parachute.

Abstract: A hollow core airfoil including a root adapted to attach the airfoil to a disk. An airfoil portion including a leading edge, a trailing edge, and a tip portion. The hollow core airfoil includes radial ribs extending from the root to the tip. Chord-wise stringers run from the leading edge to the trailing edge providing support along the chord-wise direction.

Abstract: An apparatus for regulating the height of an airship, which includes a floating body of tube-like supporting gas containers and air bags. The air bags are disposed outside and between the supporting gas containers and connect the containers to each other. The apparatus includes at least one fan-compressor for high pressure and/or at least one fan-compressor for low pressure.

Abstract: A two-sailed delta-shaped sport kite for sailing under variable wind conditions having a frame comprising a central rod having a first and a second side secured to a pair of diagonal frame members, a first perpendicular rod and a second perpendicular rod are secured to the central rod and have batten rods secured thereto. A first and a second sail of durable, flexible, resilient material are secured to the frame. The second sail is positioned in back of the first sail and is secured to the rear side of the central rod to channel air flow behind the first sail to allow for turns of extremely small radius while providing stability in both high and low winds.

Abstract: Thrusters in a propulsion system of a spacecraft spin stabilized by rotation about a spin axis are fired to increase the orbital velocity of the spacecraft in a maneuver direction along the orbital velocity vector. The propulsion system comprises a pair of thrusters juxtaposed on a common support at the periphery of the spacecraft. The thrusters have thrust axes perpendicular to the spin axis and offset relative to a transverse axis of the spacecraft by equal and opposite offset angles. Each thruster is fired separately and alternately when its thrust axis is substantially parallel to the maneuver direction while the spacecraft is rotating about its spin axis.

Abstract: A passive load limiting strut particularly useful in limiting loads between a spacecraft and an upper stage during booster first stage operation and thereby permit the launching of heavier spacecraft. The strut operates on the principle of snap through buckling of bar linkages. A tension shaft is telescoped into a compression shaft within a housing. A plurality of bar linkages are connected between each of the shafts and the housing, the bars being oriented at an acute angle in the direction of the tension shaft. In tension, the bar linkages connected to the tension shaft progressively buckle, absorbing tension loads. In compression, the bars connected to the compression shaft progressively buckle, absorbing compression loads. A compression spring intermediate the ends of the shafts further aids in load relief. Collars on the shafts prevent the shafts moving beyond preselected locations.

Abstract: A six wheel, three axle, bogie type main landing gear for an airplane is retractable as a unit and is provided with a rearward set of wheels or a forward set of wheels that is steerable with respect to the non-rotatable bogie beam. The set of wheels turns in response to steering of the nose wheel past a given angle. A wheel assembly is mounted for rotation with respect to a vertical shaft supported by a fork extending longitudinally of the beam, and a pair of hydraulic cylinders turns the wheel axles with respect to the beam.

Abstract: An acrobatic airship capable of making a perfect somersault, and a 360 degree roll in a limited small air space, without utilizing high-powered thrusters or sophisticated automatic control mechanisms. The airship has a rather thick and round axi-symmetrically shaped hull equipped with a pair of reversible thrusters on each side of the hull's nose area. Each thruster is also equipped with a tilting mechanism, which enables the thrust vector orientation to be changed independently. The airship has a set of tail fins as attitude stabilizers which do not have movable control surfaces. This acrobatic airship can be designed as a manned or unmanned craft, and is ideal for use in advertising and also as a camera platform, an observation vehicle for hazardous environments, and in various other industrial applications.

Abstract: The disclosed invention is a generic Drone Control System or alternatively method to remotely pilot an air vehicle. The present invention essentially comprises a converted aircraft or other air vehicle and a ground station from where the drone is remotely controlled. Also disclosed as part of the Drone Control System are a plurality of means to transfer information and data between the ground station and the drone.

Abstract: A quick setting and releasing system for installing and removing fixtures in a longitudinal track comprises a bottom track having an inverted, T-shaped, longitudinal channel and a fixture track having a T-shaped, longitudinal channel. The actuating and locking mechanisms comprise a pair of wing shaped lugs which float on and pivot around a longitudinal pin to lock the lugs in the fixture channel when upward pressure is applied to the pin and in the bottom track when downward pressure is applied to the pin.