Abstract: An encapsulated insulation composite system for increasing the burn through resistance of an aircraft fuselage includes: an insulation layer of glass fiber or foam insulation and a coating or interleaf barrier layer of a high temperature resistant material and/or a coating or barrier layer of a high temperature resistant material on an outer major surface of the insulation layer of the composite and a film encapsulating the composite. Preferably, the barrier layer or layers include a reflective mineral, such as a reflective mineral containing coating carried on a sheet material. Preferably, the encapsulating film is a polymeric film such as a polyimide film.

Abstract: A deployment method unfurls a plurality of flat panels interconnected by rotating hinges into a predetermined curved surface such as a spherical enclosure for use as a solar panel sphere or as any other arbitrary curved surface, for example, as a curved geodetic tent for terrestrial recreational use. Internal supporting struts and interconnecting panel frames and hinges are inflated during unfurling to automatically form the curved surface.

Abstract: On an aircraft, particularly of the commercial type, a landing gear (16) placed in front of a fuel tank (18) comprises a rod system (32) capable of coming into contact with a sliding rail (52) formed on a reinforced structural part (48) of the aircraft, in the event of accidental tilting of the gear to the rear. The deformation resulting from the rod system (32) then successively induces the complete slackening of the damper (24) of the gear, the rupture of its slack limit stop (25), followed by the rupture of a part of the rod system (32). The lower part of the gear (16) is then ejected and guided by a rear part (52b) of the sliding rail (52), with no risk of perforation of the tank (18).

Abstract: A control method and improved equatorial-normal body-stabilized spacecraft that operates in an inclined orbit. The control method controls pointing of payloads (communication antennas and instruments) and solar arrays disposed on the spacecraft. The method controls the spacecraft to provide Earth-pointing payloads and sun-pointing solar arrays so that the spacecraft body and solar arrays each rotate only around a single axis, a pitch axis of the spacecraft.

Abstract: A lighter than air airship is disclosed that has an internal weight supporting structure. The weight supporting structure allows the airship to enjoy the advantages of both static and dynamic lift. The airship disclosed herein is lifted by both lighter than air gasses as well as wings attached to the internal weight supporting structure. A cargo container for use with the airship is also disclosed.

Abstract: A pin puller combines an actuator with an anti-friction release mechanism, according to a bilaterally symmetric geometry. The anti-friction tension release mechanism ensures that only negligible friction forces need to be overcome to operate the tension release mechanism. Thus, the actuator is isolated from the large tension force that bears on the tension release mechanism. The bilateral symmetric aspect of the structure provides for mechanical redundancy, so that, in the event that one half of the pin puller fails, it is sufficient that the other half operate properly for the tension to be successfully released. This pin puller avoids premature release because it is not susceptible to static electricity or electromagnetic radiation. The pin puller also avoids generation of large shock waves due to its slow speed of operation and because of the gradual release interaction of mechanical parts within the anti-friction release mechanism.

Abstract: An aircraft having a frame (1) and at least a rotor (2a, 2b) for providing lift for the aircraft. The aircraft comprises elements for accommodation purposes. Furthermore, solar cells (5) are arranged on the aircraft for exploiting solar energy, and the rotor (2a, 2b) comprises elements for adjusting the rotor (2a, 2b) to exploit wind energy when the aircraft is substantially stationary.

Abstract: An apparatus for the suppression of infra red emissions from an engine includes a suppressor body through which pass exhaust gases from the engine, the suppressor body having an inlet means for air which is mixed within the suppressor body with the hot exhaust gases to cool the exhaust gases before final exhaustion, characterised in that at least one sonic or supersonic energy generator is provided to apply within the suppressor body, sonic or supersonic energy to enhance the efficiency of infra red suppression.

Abstract: The aircraft crew rest station for a long distance airline flight includes an overhead crew rest portion contoured to occupy the space between the curved top portion of the hull of the aircraft and the lowered ceiling of the aircraft, and an entry vestibule providing access to the overhead crew rest portion. The overhead crew rest portion includes contains one or more forward, aft, and side bunk portions. The crew rest station can be located approximately in the aircraft midsection. In one presently preferred embodiment, the overhead crew rest portion comprises forward, aft, and side bunk portions configured in cross-wise fashion. The vestibule also provides a lavatory area, as well as a closet space.

Abstract: This invention relates to a pressure stabilized inflated air transport vehicle having means for limiting crack propagation in the hull envelope whereby leakage of the gas in the haul due to the crack will not exceed the gas pressure maintaining means.

Abstract: A twin turbine engine helicopter has a two-stage main reduction gearbox, the input stage having a speed reduction ratio exceeding 5.5:1, into an epicyclic gear train second stage ratio about 6:1 for approximately 30:1 or higher overall ratio output to the main rotor. In various embodiments, the first stage uses face gears, or bevel gears, with a reduction greater than 5.5:1 and a second stage epicyclic gear train using single or double row helical or spur gears. The first stage gears are straddle mounted in the housing.

Abstract: In an adjusting apparatus for control surfaces of a missile the control surfaces 2, 3 are displaceable by adjusting motors 5, 6 by way of thrust spindles 15. To afford a compact structure and a low weight the stators 7 of the adjusting motors 5, 6 are arranged directly in a carrier housing 4 and the thrust spindle 15 engages into a female thread 14 of the motor shaft 9.

Abstract: An accurate and compact flap skew detection system that operates independent of the flap-drive system comprises, in a preferred embodiment, three major elements; a rotary position sensor located on fixed wing structure; a push-pull link and crank arm to convert translational flap motion into rotary sensed motion at the sensor; and a computer processing means to process the rotational sensed information and to compute a flap skew algorithm. Inter-flap and intra- flap translational motion is sensed and compared using a plurality of rotary sensors. Sensors falling outside of predetermined limits or violating control law rules indicate a non-synchronous or asymmetrical “skewed” condition.

Abstract: A thrust mount includes a platform mountable to an aircraft pylon, and includes end clevises and a center clevis therebetween. An equalizer lever includes opposite ends, and a center therebetween pivotally joined to the center clevis. Thrust links are pivotally joined to the lever ends. And, a pair of elastomeric snubbers are disposed adjacent respective ends of the lever inside the end clevises in frictional abutment therebetween.

Abstract: A momentum control system for driving the momentum of a spinning spacecraft to zero while it spins around a sunline. The system includes a sun sensor for determining the position of the sun, a suite of tachometers for determining the momentum stored in the spacecraft, and a stored movement sensor. Each of the readings from these sensors is fed to a controller. The controller also monitors the magnitude of the spacecraft overturning momentum and the windmill momentum. If the overturning momentum is outside acceptable limits then the rotation rate of the spacecraft is modulated to drive the overturning momentum towards zero. If the windmill momentum exceeds acceptable limits, the angle of the solar panel is adjusted to drive the windmill momentum towards zero.

Abstract: The invention concerns a vertical take-off and landing aircraft (10) with a plurality of lift (26a-26p) and thrust rotors (20a,20b), in which all rotors have their own electric motor (48a-48p,50a,50b) as a drive.

Abstract: A bi-directional pilot parachute release assembly (10) for use with a conventional parachute arrangement (100) including a dual compartment parachute enclosure member (101) having an upper compartment (102) and a lower compartment (103) provided with a bottom panel (104) that is operatively associated with a pilot parachute member (40) dimensioned to be received in a storage unit (11) including a storage panel member (20) having an elongated generally centrally disposed mouth opening (23). The top of the pilot parachute member (40) is provided with a cap member (50) having widely spaced opposite ends (51) provided with hand grip elements (52) that will allow the pilot parachute member (40) to be withdrawn from the storage unit (11) in either a right handed or left handed fashion.

Abstract: A bellows body is curved and formed with a plurality of convolutions to allow axial and lateral flexure of both ends of the bellows when connected between the engine exhaust stack and an airframe duct. The upper slotted end of the bellows fits over the stack nipple and is conventionally, fixedly sealingly secured thereto by an O-clamp. The outside diameter of the lower end forms a gas tight slip joint in the bore of the lower cowling heater duct flange. For added reinforcement an optional collar may be permanently fitted exteriorly and/or interiorly of the stack wall adjacent the stack nipple and an optional brace may be welded interiorly between the stack and scupper.

Abstract: The present invention relates to a device (1A) for controlling a hybrid countertorque system of a helicopter (He), which comprises a countertorque rotor (R2), and at least one aerodynamic steering surface (D). According to the invention, said device comprises means (1A) for controlling, as a matter of priority, the aerodynamic surface (D) so that it generates lift which represents at least part of a first control command, which can be executed by said surface (D), and to control the countertorque rotor (R2) in such a way that the combined action of the surface (D) and of the rotor (R2) represents a command for controlling the helicopter (He) in terms of yaw.

Abstract: Apparatus for damping vibrations of a structure such as the air frame of a helicopter wherein a spring system (1), which has an elastic wall structure forming a tube-shaped hollow body supports a weighted vibrating object (23). At least one region of the wall structure is constructed to be elastically deformable in its plane, with a spring stiffness, tuned to the frequency of the vibration to be damped. The wall structure is formed by several planar spring elements (11a, 11b, 11c, 11d), each of which can be elastically deformed in its plane by an arrangement of longitudinal strips (110a, 110b, 111a, 111b) and connecting cross pieces (120a, 120b, 121a, 121b). A battery of the helicopter can be used as the vibrating weight (23). The vibration damper containing the battery is installed at a location on the helicopter where clear structural vibrations occur in two directions perpendicular to each other and wherein the vibration damper is tuned to the vibrations frequencies in both directions.