Abstract: A sailboat davit connectable into the ground adjacent a seawall, water's edge or other like supportive objects for lifting and lowering a small sailboat. The device includes an elongated upright support member having a radially outwardly extending boom connected at one end to the upper end of the upright support member. A generally horizontal spreader beam is connected at a mid-point thereof to the distal end of the boom so that the spreader beam extends in either direction preferably from a plane generally defined by the upright support member and the boom. A flexible cable and pulley arrangement, winch-activated, is provided having a flexible cable downwardly extending over a pulley at each end of the spreader beam, each end of each cable being connectable to the sailboat hull whereupon the sailboat is lifted and lowered in response to winch activation.

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 scanning sensor having a radiation detector is mounted on a spacecraft or satellite orbiting the earth. The scanner is pointed in such a way with respect to the orbit plane of the satellite that the instantaneous field of view of the detector crosses the region between the lower and upper limits of the travel of a celestial body in a year in order for the radiation detector of the earth sensor to encounter the celestial body at least once per orbit. Electrical signals based on the horizon crossing and the presence of a celestial body in the field of view of the detector are generated and used to derive Yaw, Pitch and Roll attitude information for the satellite with respect to the earth.

Abstract: The variable speed drogue for use with an inflight aerial refueling system includes a refueling coupling for receiving a refueling probe. A plurality of trailing edge support arms are pivotally mounted to the trailing edge portion of the refueling coupling, projecting rearwardly, a plurality of pivot linkage members are pivotally connected to the trailing edge portion of the refueling coupling, and a plurality of leading edge support arms are pivotally connected to the pivot linkages. A mechanism is also provided for uniformly and symmetrically longitudinally changing the pivot points of the leading edge support arms to change the projected area of the drogue canopy.

Abstract: An improved fly by wire or fly by light system which provides for a smooth manual override of the autopilot function by allowing the pilot to modify the autopilot command to the control surfaces by physically manipulating the yoke to a position different than that commanded by the autopilot.

Abstract: A method of sun search and acquisition is disclosed for a spacecraft (18) which is stabilized in three axes. The method utilizes three axes gyro rate and integrated rate sensing together with three simple slit type sensors (10, 20, 30, 40). The method starts from an arbitrary attitude and from body rates up to the limits of the gyro rate sensors and is comprised of a rate nulling step followed by two consecutive simple search procedures. One search procedure is about the pitch axis until alignment of the sun with the roll/pitch plane and the other search procedure is about the yaw axis until alignment of the sun with the roll axis. The sun acquisition culminates in pointing the roll axis of the spacecraft (18) toward the sun. By using slit type sun sensors (10, 20, 30, 40) versus a wide field of view sensor it is easier to find a mounting location on a spacecraft (18) which is free from spurious reflections off other parts of the spacecraft.

Abstract: An aircraft ski for attachment to the axle of the ground wheel of the aircraft includes a pair of rams moving the ski upwardly and downwardly from a retracted position to a deployed position. On each side of the ski is provided a respective lever which is connected to the axle and extends therefrom rearwardly to a rear end of the ski. Intermediate the length of the lever is provided a cross torque tube which prevents twisting movement of the ski as it is deployed. At a rear end of each of the levers is provided a cross shaft which is attached to the rear end so that the cross shaft is rotated as the lever moves with the deployment of the ski. The cross shaft is attached to a rear restraint cable which is thus paid out and drawn in respectively by the movement of the ski between the deployed and retracted positions. A front restraint cable extends from a forward end of the ski to the aircraft.

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: 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: This invention outlines excitation means to transform the linear momentum of an underwing energized jet into rotational form in a selective manner to provide an asymmetric shear layer to increase compression wave reflection from the forward undersurface of a supersonic wing. The wing compression energy is thereby recovered into useful work as an increase in pressure on the upward reflexed wing backside. The upper surface of the shear layer is comprised of an array of vortices whose rotation is opposite to the wing circulation, providing the required angular momentum reaction. The upper wing surface is flat to avoid generation of waves and an adverse angular momentum reaction above the wing. The vortices below the wing are compressed by the underwing pressure, comprising a pressure shield to enhance the reflection.

Abstract: A space shuttle wheel acceleration system includes a plurality of attachm bands located in the grooves of a tire and extending around the circumference of the tire with collapsible cups attached to the attachment bands located at spaced intervals around the tire that pop open on the downwind portion of a tire revolution to catch the wind and rotate the tire and collapse on the downwind portion of a revolution to reduce drag. The cups include elastic-bands to maintain the cup in a collapsed state when not catching the wind and also include stiffeners to prevent the cups from folding over when catching the wind. A breakaway buckle attaches the ends of each attachment band and automatically fails when the tire touches down to shed the space shuttle wheel acceleration system for smooth runway performance.

Abstract: An engine inlet having strakes for landing speed reduction on a trapezoidal wing shaped aircraft, specifically the T-38. The strakes are mounted on the engine inlet just forward of the wing leading edge and well above the wing plane. The preferred strakes have an area greater than 3% of the wing area and are uncanted with respect to the wing. Use of the strakes forstalls wing buffet, yet exhibits well behaved longitudinal stability at high angles of attack thereby allowing operation of the aircraft at higher angles of attack and associated higher coefficients of lift, such as during landing, resulting in a reduction of the landing speed of the aircraft. Various strakes in the placement thereof are disclosed.

Abstract: An air spring structure, for preventing the shaking of a suspended rotator by absorbing/preventing the vibrations of the rotator in a commercial or household machine, comprises a body made of soft rubber materials, the body being provided with an inner cylindrical and outer cylindrical portion and an upper and lower supporting portions to thereby form an annular air chamber therein, a longitudinal through hole being defined by an inner cylindrical portion at the center. The hardness of the soft rubber materials forming the body are below 30 to 40 Shore (A). The thicknesses of the inner cylindrical portion and the outer cylindrical portion are thinner than those of the upper and lower supporting portions, and the ratio of horizontal stiffness (kh) to vertical stiffness (kv) is between 0.7 to 1.

Abstract: The disclosed invention is a regulated drag area parachute for decelerating manned ejection seat or an ejectable capsule at a low altitude from an aircraft or other air vehicle. This parachute comprises a canopy composed of two portions, suspension lines, and a means for controlling the inflation of the canopy so that the two portions of the canopy inflate independently from one another. This means for controlling the inflation of the canopy provides a manner to regulate the rate of inflation of the lower portion of the canopy. Thus, the invention allows the top, or apex portion of the canopy, to inflate rapidly while the remaining portion of the canopy can be inflated subsequently and in a controlled manner so that the effective drag area of the canopy can be regulated during the deployment of the parachute.

Abstract: First and second cargo racks are mounted on opposed sides of the cockpit entry opening on a kayak deck to mount cargo relative to the kayak structure when limited cargo space is available within the kayak. The first and second racks include pairs of rail members mounted to supporting posts to fixedly secure the rails relative to the deck of the kayak member.

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 lift augmentation system for aircraft which comprises a plurality of propellers parallel to an aircraft wing and inset parallel to and at the trailing edge of the wing. The propellers function to both directly produce vertical lift in the manner of helicopter blades and to augment air circulation over the wing to enhance lift produced by the wing. The propellers are set into the trailing edge of the wing along the length of the wing, with the inboard propellers preferably closely spaced to the fuselage to force air flow over the reducing taper of the fuselage. Each propeller is tiltable in all directions about a vertical axis through the propeller hub and the assembly of engine and propeller is hinged to the wing for pivoting in a plane substantially parallel to the aircraft axis.

Abstract: A space launch system and a space transfer vehicle usable within such system. The space transfer vehicle includes a primary propulsion engine and attitude control system. A guidance system for both the atmospheric launch vehicle and the space transfer vehicle is integral with the space transfer vehicle.

Abstract: A hitch for attaching a trailer to a bicycle comprises a mounting bracket adapted to be releasably attached to a chain stay of the bicycle frame and a resiliently flexible coupling member of an elastomeric material attached to the mounting bracket and adapted to be attached to a boom tube that is in turn attached to the trailer. The coupling member provides universal articulation between the mounting bracket and the boom tube.