Abstract: A generally toric lighter-than-air gas bag-type airfoil is tethered to the ground at a plurality of angularly widely distributed points about the periphery of the gas bag. A wind turbine is mounted at the entrance to the axially central vent. The tether lines are entrained about individually operable power winches, preferably controlled by a microprocessor which takes in wind direction and tether line tension data and operates the winches and inflation gas inlet and outlet valves to orient the wind turbine into the wind for maximum power output.

Abstract: A water-activated canopy release mechanism having a detachable sleeve positioned between the arms of a buckle yoke. The sleeve contains a longitudinal passage having a release piston and bushing positioned therein and supporting the sleeve within the yoke. An explosive cartridge mounted at the piston end is fired by a sensor activated by water of predetermined conductivity and drives the release piston completely into the sleeve and wedges it there, thus freeing the end of the sleeve adjacent the cartridge. Simultaneously, the piston drives the bushing out of the other end of the sleeve and against a wedge carried by the yoke arm. As a result, both the piston and the bushing are held in a position which permits the sleeve to drop free of the yoke releasing the canopy from its load.

Abstract: An annular wing particularly suited for use in supporting in flight an aircraft characterized by the absence of directional stabilizing surfaces. The wing comprises a rigid annular body of a substantially uniformly symmetrical configuration characterized by an annular positive lifting surface and cord line coincident with the segment of a line radiating along the surface of an inverted truncated cone whereby a decalage is established for the leading and trailing semi-circular portions of the body, relative to instantaneous line of flight, and a dihedral for the laterally opposed semi-circular portions of the body, relative to the line of flight, the direction of flight and climb angle or glide slope angle being established by selectively positioning the center of gravity of the wing ahead of the aerodynamic center along the radius coincident with an axis for a selected line of flight.

Abstract: A tow plate including a retention assembly and a removable clevis assembly made up of a main clevis member and a drogue clevis member engageable with the main clevis member. A first latch mechanism latches the main clevis member to the retention assembly. A second latch mechanism latches the drogue clevis member to the main clevis member. To effect force transfer, the entire clevis assembly is released by unlatching the main clevis member from the retention assembly, with the drogue clevis member latched to the main clevis member. To effect drogue jettison, the drogue clevis member alone is released by unlatching it from the main clevis member, while the main clevis member remains latched to the retention assembly.

Abstract: A watersled towed behind a moving boat is steerable from side to side by a rider pulling on or releasing the handle on a single control rope which is attached to a tow rope. The handle is held at various positions by two cleats connected to a raised section of the top deck of the sled between the rider's legs to facilitate proper operation of the sled. The tow rope is attached to the rear of the sled by being passed through an opening in the hull and knotted. The tow rope is held in proximity to the bottom of the sled by passing the rope through a plastic slide configured to travel within a groove extending the width of the sled. The groove is shaped in an arc having a center at the tow rope attachment point and has end closures to prevent the slide from leaving the groove. The control rope is held forward of the tow rope attachment point by a knot in the tow rope.

Abstract: A propulsion system for an airplane to permit it to achieve vertical and/or short take-offs and landings. The propulsion system is integrated into a wing/nacelle unit and includes a thrust vectoring system. A separate flow turbofan engine is mounted in each wing/nacelle unit. A system of three flaps is located at the rear of each wing/nacelle unit for deflecting the turbofan engine exhaust downward, rearward, or any angle in between. These three flaps are arranged to provide a main thrust nozzle in the horizontal flight position without any additional flaps between them. One flap is located at the wing/nacelle upper surface trailing edge. Two slots are provided at the leading edge of this flap. The upper forward most slot is provided as an exit nozzle for the engine turbine exhaust, which is shrouded from the fan exhaust. The second of these two slots removes a portion of the high energy fan exhaust from the fan discharge duct and ejects it over a flap upper surface.

Abstract: A spacecraft specifically adapted for launch from the space shuttle by means of a cradle having locking and ejection mechanisms mounted therein. The cradle fastens into the payload bay of the space shuttle and returns therewith for reuse in subsequent launches. The spacecraft mounts at three points to the cradle, and the cradle mounts at three points to the shuttle such that a plane through the attachment points passes through the roll axis of the spacecraft at approximately the center of mass thereof. The cradle utilizes the truss structure of the spacecraft to produce the required stiffness by providing a structural tie between the two ends and the bottom of the cradle. At launch, the spacecraft is ejected with both linear and angular momentum, the spin providing gyroscopic stability. The locking mechanisms in the cradle can be remotely controlled to relock the spacecraft to the cradle in the event of an unsuccessful deployment attempt.

Abstract: A device for locking the ailerons and elevators of an aircraft controlled by a wheel-operated longitudinally shiftable and rotatable control column, and, at the same time preventing theft of the navigational instruments and radio equipment mounted on the instrument panel in the cockpit of the plane. The protective device takes the form of a cover formed of two overlapping plates having an arrangement for adjusting the overall width. The adjusted cover is mounted immediately adjacent the instrument panel by means of upper and lower clamping blocks secured about the control column in such a manner as to prevent unauthorized movements of the column and access to the instruments on the panel. The blocks have complementary semi-cylindrical grooves which clamp about the control column, and one block is fixed to the cover plate while the other is hinged to the first for ready uncoupling and coupling movements.

Abstract: A satellite maintenance system for satellite stations orbiting in the geosynchronous corridor comprising a roving satellite maintenance vehicle capable of operating autonomously in the geosynchronous corridor and containing replacement hardware in modular form by which maintenance operation can be made on the satellite station by the exchange of one module for another thereby repairing or upgrading the hardware in the satellite station to prolong its useful life. The maintenance vehicle is capable of operating in the corridor for prolonged periods of time in a standby mode and capable of proceeding, on command, to the satellite station to perform the maintenance function automatically.

Abstract: There is disclosed an airplane having an inflatable type air cushion confining undercarriage thereunder wherein the airplane wing structures comprise three-dimensionally enlarged inner wing components merging aerodynamically with the airplane fuselage. The under surfaces of the inner wing components and the fuselage cooperate to provide a downwardly convex broad base structure which is oval-shaped in planform, and a toroidal configured inflatable trunk is attached to the perimeter of the base structure for circumscribing the air cushion cavity under the airplane. Thus, an enlarged width and length air cushion type undercarriage is provided to give the airplane improved stability characteristics when operating in air cushion, ground, or water supported mode. When the trunk system is deflated the elastic sheet material thereof retracts snugly against the slightly convex bottom surface of the base structure.

Abstract: Aircraft safety apparatus includes front and rear parachutes mounted at the front and rear portions of the aircraft for adding to the buoyancy thereof during emergency landings. Devices are provided for moving the parachutes into their operating positions. A plurality of auxiliary jet propulsion units containing fluid under pressure propel the aircraft to aid in its manueverability should the aircraft malfunction in flight, as well as during emergency landing procedures. At least some of the jet propulsion units are directed transversely to the body of the aircraft to direct fluid under pressure laterally to cause lateral reaction movement of the aircraft for steering purposes while the aircraft is descending under parachute assist.

Abstract: A device for starting an aircraft engine which is capable of being started by rotating a propeller connected to the crankshaft of the engine. The device comprises an anchor device for fixedly positioning on the landing surface below the propeller; this anchor device can be held in place by a portion of the aircraft itself; in one case, the nose wheel and in another case, a separate extension arrangement. A holding device is provided for connection to the anchor device for holding the propeller and the crankshaft of the engine against rotation in a proper starting position while a rotative device is provided for connection to the anchor device for placing a biasing force on the propeller for rotating it. The anchor device has forwardly extending arms, or members, with an attaching device fixed below the propeller, the holding device and rotative device are each fixed between the propeller and the attaching device.

Abstract: A mounting grommet intended for use in bores having sharp corners. The grommet includes a sleeve of hard material and a tubular, elastomeric element extending about and along the length of the sleeve. The element includes a cylindrical shank terminating at one end in an enlarged head. An axially extending recess is disposed in the head at its interface with the shank and the head has a generally frusto-conical surface on its side opposite the recess, the radially outer portion of the frusto-conical surface being located intermediate the ends of the elastomeric element. When applied to a bore in a rigid element having sharp corners, and compressed, the construction causes the recess to deflect radially inwardly at the corner so that there is no contact between the elastomeric element and the corner that would cause premature failure of the grommet.

Abstract: The guard retains the cable on a pulley of a cable control system that indes another pulley mounted on a pivotable radius arm for swingable movement relative to it. Usually, the swingable pulley is linked to a third pulley mounted on a hinged structural member which itself swings with the radius arm to and from `closed` or `open` positions. When the arc is wide, i.e. around 180.degree., conventionally mounted guards engage and bind the swinging cable. The present guard is an elongate member pivotally mounted on the radius arm. In the `closed` position, a retaining flange formed on the guard moves for cable retaining purposes into close proximity with the fixed pulley and the proximity or clearance can be adjustably fixed and locked by an eccentric stop. During the `opening` swing, the cable engages the guard which then pivots sufficiently to prevent the undesired binding. The pivotal range of the guard is restricted by a pin and slot arrangement.

Abstract: A series of flaps along the leading edge of a highly swept-back wing for a supersonic airplane; wherein, the spanwise series of flaps comprise a double-flap chordwise having fore and aft flap segments. When the leading edge double-flap is positioned at a forward and downward angle-of-deflection relative to the wing, the foreflap segment is further positioned at an angle-of-deflection relative to the aft-flap segment. This difference in the deflection angles, between the fore-flap segment and the aft-flap segment, creates a vortex flow region ahead of the wing leading edge; and this vortex functions to control separation of an upper surface boundary layer airflow, over the remainder of the upper surface of the wing. Also, the vortex flow will move in a spanwise direction outboard toward the tip of a swept-back wing, while remaining forward or ahead of the upper surface of the aft-flap segment.

Abstract: This shock absorber strut incorporates an annular piston between the lower and upper bearings of the shock absorber piston; together with a separator piston in the bore of the shock absorber piston. The volume below the separator piston is filled with hydraulic fluid and is connected to an external hydraulic power source. An external hydraulic power source is also connected between the annular piston and the shock absorber lower bearing. Application of external hydraulic pressure to the underside of the annular piston, while simultaneously draining off fluid below the separator piston, causes the shock absorber to contract. The volume vacated by the fluid below the separator piston provides a reservoir for displaced shock absorber fluid which pushes the separator piston down the bore of the shock absorber piston. The contracted strut is then locked hydraulically. The procedure is reversed for shock absorber extension.

Abstract: The device retains the ejection seat arm/dearm lever in safe position to allow the seat to be tilted safely for required maintenance and repair work. A bolt positioned through a clearance hole in an inverted U-shaped base member engages threads in the ejection seat structure. An upstanding brace extends upward from one end of the base member at an angle to abut the seat ejection arming lever to physically block and prevent its movement into the armed position. The bolt is retained in the base member by a cotter pin through the body of the bolt under the head to allow turning while preventing separation from the base.

Abstract: Disclosed herein is an oar lock seat device that combines a sliding oar lock unit with an adjustable seat-cooler box. This apparatus is comprised of two gunnel mounted sliding oar lock assemblies structurally connected by an adjustable seat-carriage assembly whose unique construction encompasses an insulated storage box upon which the occupant sits. This apparatus fits securely into inflatable rafts of various dimensions and will remain with the craft even in an inverted position.

Abstract: In a stern drive for watercraft, of the type using a gimbal ring to support the external propulsion unit, the gimbal ring is provided with an upper vertical square bore, a slot across the bore, and clamping bolts to provide full engagement with the square sides of a steering swivel shaft.

Abstract: A kite-like flying device includes a sail, a keel stick with a larger resilient member at its leading end, and wing sticks connected to the opposide ends of a smaller resilient member the midportion of which extends laterally through the larger member to provide a resilient resistance to forward movement of the keel stick. A cross stick is flexed and received by sockets which are slightly inclined relative to each other in connector blocks slidably mounted on the wing sticks. Two strings extend from the operator to a control rod which is connected by a string harness to the kite. The connectors for connecting the strings to the control rod each include three bores through which the strings pass back and forth to provide on each side thereof a loop and an extending string portion which passes through the loop so as to be frictionally retained when tension is applied to the opposite extending string portion.