Abstract: In an airborne vehicle utilizing tail fins to provide directional control by use of the sideslip maneuver, a variably positionable side force generator airfoil that is positioned in response to the normal load factor of the vehicle to eliminate undesired roll caused by sideslip.

Abstract: An isolator with improved uniform spring characteristic response resists transmission of shock and vibration forces between structures, and includes a plurality of arched, individual, flexural support elements arranged circumferentially about an upright axis and spanning the distance between a base connectable to one of the structures, and an elevated support connectable to another of the structures.

Abstract: A retractable helicopter rotor in which the rotor and its blades, the swashplate and the pitch change rods are retracted and extended as a unit during the helicopter rotor retraction/extension mode of operation, wherein the connection between the rotor support system and the fuselage constitutes a single interface between overlapping circumferentially extending flanges of each, and with the bolts joining those flanges being loaded in compression.

Abstract: A rotary wing aircraft with rotor blades mounted on a rotor head and with reaction drive. The rotor blades have hollow interiors and are provided on their trailing edge with at least one outlet opening for compressed air supplied via the rotor head. Such rotor head may include an air suction region in which there is mounted a suction device having a pressure side connected to the hollow interiors of the rotor blades.

Abstract: An assembly is provided for use with a trailer including a plurality of wheels, normally engaged air brakes coupled to the wheels, and an air supply line coupled to the air brakes for supplying air to release the air brakes. The assembly includes a valve for selectively venting the air supply line to the atmosphere to prevent the release of the air brakes from their normally engaged position. The valve is coupled to the air supply line and is adjustable between a first position and a second position. In the first position, the valve seals the air supply line to permit the air brakes to be released when air is supplied to the air supply line. In the second position, the valve vents the air supply line to the atmosphere. When the valve is in its second position and air is supplied to the air supply line, the air is vented to the atmosphere. Therefore, in the second position, the valve means prevents the air brakes from being released when air is being supplied to the air supply line.

Abstract: A heavy launch vehicle for placing a payload into a spatial Earth orbit including an expendable, multi-container, propellant tank having a plurality of winged booster propulsion modules releasably disposed about one end thereof; and a payload supported by adapter structure at the other end. The preferred payload is an entry module adapted to be docked to a space station and used as a return vehicle for the space station crew, as scheduled, or in emergency situations. Alternately, the payload may include communication satellites, supplies, equipment and/or structural elements for the space station. The winged propulsion modules are released from the expendable propellant tank in pairs and return to Earth in a controlled glide, for safe landing at or near the launch site and prepared for reuse. The rocket engines for each propulsion module are dual-fuel, dual-mode engines and use methane-oxygen and hydrogen-oxygen, respectively, from the multi-containers of the propellant tank.

Abstract: The invention is a rig useful in preventing relative movement between two hicles or other payloads suspended from a helicopter. The rig has two triangular plates which are in connection between the vehicles, the connection being loose before cables from the helicopter to the triangular plates are tensioned. When the helicopter rises, tension on the cables raises the triangular plates, thereby pivoting clevises which are engaged with the triangular plates and which are mounted on on the vehicles. The pivoting of the clevises draws the vehicles into tight abutment with abutment plates at the ends of the triangular plates so that the vehicles act as a single, more stable load. A cross member is connected both between the triangular plates and between the vehicles to inhibit relative lateral movement of the vehicles.

Abstract: A reservoir for aircraft, such as a helicopter, containing a fluid and having at least orifices in its side wall close to its bottom and to which a fluid feed and return ducts can be connected. The reservoir has to allow the aircraft to effect temporary flight phases under negative load factor, a plate having a passage, for retarding the movement of the fluid contained in the reservoir, so that the fluid, moving from the bottom to the top of the reservoir during the temporary flight phases and passing through the passage of the retarding means, remains in communication with the orifice for the duration of the flight phases, while avoiding the entry of air into the duct.

Abstract: A satellite comprising a deployable solar generator that can be oriented relative to the satellite body is kept facing the sun at all times. It includes an attitude stabilization device comprising a superconductive material closed loop carried by a support coupled to the solar generator and disposed on a side of the support facing substantailly away from the sun. A secondary loop parallel to the closed loop is substantially the same shape and size as the closed loop, and is carried by the support near the loop. A resistive circuit is carried by the support near at least part of the closed loop. A selective electrical power supply circuit is connected electrically to the secondary loop and to the resistive circuit.

Abstract: A suspension system for linear reciprocating device which allows a relatively large axial stroke while also providing long life and high torsional and radial stiffness. The system consists of a grounded ring to which pairs of substantially coplanar cross straps are connected about an axis of symmetry around the ring. The midpoints of the straps are attached to the reciprocating device. In operation the flexing of the straps in combination with the distortion of the grounded ring allows for a greater axial stroke within a smaller perimeter than using flexing straps alone. This allows the suspension device to be utilized in a much smaller area providing further advantages in application.

Abstract: A pitch stabilization system for an ejection seat includes a gyroscope rotor assembly having a pinion gear attached to two rotor wheels. The rotor assembly is mounted with a geometry to precess in response to change in the pitch rate of the seat. Precession of the gyro rotor rotates a vernier rocket with the resulting thrust applying a correcting moment to counter the adverse moment causing the ejection seat to pitch. When the seat is at rest in the cockpit of the aircraft, the rotor pinion gear teeth engage the teeth of a rack mounted stationarily to a fixed attach point on the aircraft. When an ejection force is applied to the seat, by a catapult or the like, the rotor wheel is rotated by virtue of the interengaging relationship between the rotor pinion gear teeth and the rack teeth so that by the time the ejection seat exits the cockpit the rotor disengages from the upper end of the rack, and is fully spun to operating revolution so that it can precess gyroscopically.

Abstract: An attitude control device for a satellite stabilized on three axes including a pitch axis comprises two solar generator wings extending in opposite directions away from a satellite body on respective longitudinal axes at least approximately parallel to the pitch axis. Two drive motors drive these wings independently of each other in rotation about rotation axes at least approximately parallel to the pitch axis to keep the wings facing the Sun with a depointing angle at most equal to a predetermined maximum depointing value. Sensors measure attitude angles and a computation system commands the drive motors according to the attitude angles. On each wing an additional surface in the form at least one vane extends longitudinally beyond the end of the wing parallel to its longitudinal axis. These additional surfaces have substantially the same surface area and are inclined about this axis relative to the wings in opposite directions by at least approximately the same angle which is less than the 90.degree.

Abstract: A two-string stunt kite has a diamond shaped sail, a longitudinal keel strut, and a bowed cross strut disposed in a plane which is oblique to the keel strut. Left and right bridles are provided, each of which includes a first string attached to a forwared point on the keel strut, a second string attached to an aft point on the keel strut, and a third string which is attached to a point on the cross strut, inboard of the bridle's respective left and right wingtip.

Abstract: An ejection seat (1), supported on ejection gun guide rails (2) and moveable between an upright position to a reclining position thus affords the pilot greater protection from the effects of high "g" forces. Movement of the seat (1) is effected by hydraulic acutators (3), (4), guided by an arcuate track (15). The invention has the further advantage of allowing ejection from an upright or a reclining position or any intermediate transitional position.

Abstract: The "Lift Back" is an invention for providing spinal protection with an impact resistant moldable material for insertion in a fabric harness in sport aviation particularly Paragliding. The invention is comprised of two main parts which are fastened together and in union provides relief to the low back, rib cage and shoulders from the stress put on the body while the pilot operates his Paraglider, and most importantly provides spinal protection to the pilot's spinal column in the event of impact.

Abstract: An air spring having a sleeve-like flexible member made of elastomeric material. A beadless end portion of the flexible member is attached to a mount by being clamped between the mount and a clamping piece. The mount and the clamping piece have conical clamping faces which coact to provide a reliable attachment which is easy to assemble. The conical clamping piece is arranged so as to be axially displaceable in the mount to conjointly define a clamping gap with the mount. The clamping piece closes the clear cross section of the end portion of the flexible member in an airtight manner.

Abstract: A parachute canopy seam joint for fastening a ribbon seam and a radial seam of a parachute canopy together. This parachute canopy seam joint combines a ribbon seam using a zigzag stitch pattern and narrow strips of radial tape sewn together with multiple rows of a straight stitch pattern. The ribbon seam attaches two overlapping ribbons within the parachute. The narrow strips of radial tape shroud the ribbon seam which result in a high strength and low weight and volume radial seam and seam joint. This new configuration of a parachute seam joint has distinct advantages in terms of strength and shock absorbing capacity. Specifically, this new parachute seam joint has a seam strength equal to or greater than the minimum rated strength of the adjoining materials and employs a smaller weight and volume of material than conventional radial seams and seam joints.

Abstract: A fluid-filled elastic rotational coupling including an inner and an outer sleeve fixed to one and other of a driving and a driven rotary member, an intermediate sleeve disposed in concentric and radially outwardly spaced relation with the inner sleeve, a pair of wings extending diametrically opposite parts of the inner sleeve toward the intermediate sleeve, an elastic body interposed between the inner and intermediate sleeves and having two pairs of pockets each pair being formed on opposite sides of each wing as viewed in the circumferential direction of the coupling, and a sealing rubber layer between the intermediate and outer sleeves. The outer sleeve closes the pockets to thereby provide two pairs of fluid chambers. An orifice passage is provided between the intermediate and outer sleeves, for fluid communication between each pair of fluid chambers whose fluid pressures change in opposite direction upon relative rotation of the inner and outer sleeves.

Abstract: A thrust reverser for aircraft fan jet engines using a plurality of sets of deflector and blocker doors filling openings through the engine nacelle during normal engine operation. During thrust reversal, the doors substantially block air normal fan air flow through the duct between engine cowling and the outer nacelle and deflect it out through the nacelle openings in a reverse direction. An actuator and hinge assembly moves each blocker door from a stowed position flush with the inner nacelle surface to a deployed position blocking air flow between nacelle and cowl. Simultaneously, an actuator and hinge assembly moves each deflector door from a stowed position flush with the outer nacelle surface to a deployed position receiving air from the blocker doors and deflecting that air flow in an outwardly and forwardly direction. The actuator and hinge assemblies are substantially out of the path of air flow in both the stowed and deployed positions.

Abstract: A geostationary satellite system includes an operational satellite and a spare or back-up satellite, characterized in that the spare or back-up satellite is located in a geostationary orbit (3) at the same mean longitude as the operational satellite, with the inclination and eccentricity of the spare or back-up satellite orbit (3) being non-zero, and with the apse line (4) of the spare or back-up satellite orbit (3) being close to, or coincident with, the node line, so that the spare or back-up satellite can be co-located with the operational satellite with minimal risk or collision or communications interference therewith.