Abstract: A bogie type landing gear especially suitable for providing soft landing capabilities for short take-off and landing (STOL) aircraft wherein fore and aft wheels are mounted on opposite ends of a bogie which is pivotally attached to the lower end of a vertical shock strut. In one embodiment, a torque link pivotally connects the aft end of the bogie to the shock strut such that, under normal landing conditions, the front wheel will touch down first thereby reducing and directing the landing forces to minimize shock to the aircraft. The aft mounted torque links also act as a tension member during the initial landing stroke. In another embodiment, a damper acts as a tension stop for a soft landing arrangement as well as to dampen bogie motion over bumps with the torque links being separate.

Abstract: High velocity impact landing forces are attenuated in apparatus (10) utilizing an energy absorbing tube (12) of composite fibrous material, that is, a fiber reinforced plastic. The energy absorbing tube (12) is disposed in force transmitting relation between an anvil (14) disposed at one end and structure (16) for applying a force to the opposite end of the tube (12) to provide force attenuating apparatus. The tube (12) is progressively crushed onto the anvil (14) by the force applying structure (16) to dissipate energy. The force attenuating apparatus (10) is used in an energy absorbing seat (20) to provide occupant protection against high impact forces. Other uses of the force attenuating apparatus (10) is in a landing gear mechanism (76) and a vehicle bumper system (89).

Abstract: A load support is arranged to be connected to a parachute and has a center guide tube slidably receiving a landing rod. This landing rod is of a sufficient length to project beyond the lower end of the guide tube so as to engage the ground ahead of the load support. A slidable friction connection is provided between the landing rod and the load support for cushioning the landing shock of such support. Brake pads are used as the friction connection, and such brake pads are associated with adjustment apparatus comprising a rotatable holder for the brake pads and a cam and cam follower assembly which serves to adjust the compression of the brake pads on the rod upon rotation of the holder. A pinion and gear connection is provided between the holder and the support to provide the rotatable adjustment.

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 detecting a hard landing of an aircraft. The aircraft is equipped with a detector for determining the vertical acceleration produced by the impact of the airplane with the ground. The device is equipped with a threshold trigger for indicating when acceleration exceeds a predetermined level corresponding to a hard landing.

Abstract: A helicopter landing gear assembly includes a pair of crosstubes (20, 22) having a pair of struts (28, 30) connected at the outboard ends thereof. A first of the crosstubes (22) is connected to the helicopter fuselage (16) at a pair of laterally spaced points (24, 26). The second of the crosstubes (20) is joined by a pivot connection (32) to a structural bridge (10) positioned above the second crosstube. The structural bridge (10) is connected at its outer ends to the fuselage main beams (12, 14). The structural bridge (10) connected to the second crosstube (20) permits the helicopter fuselage (16) to pivot about a fore-aft axis thereof to lower the natural roll frequency of the helicopter airframe and therefore increase the margin of stability to prevent ground resonance.

Abstract: A launch platform for conventional landing gear aircraft having the launch platform configured as a ram wing structure with wheel latches secured to the platform. The platform is secured to the aircraft by means of the wheel latches. The wheel latches are released to permit the aircraft to leave the platform by pilot command. A parachute system is provided for platform deceleration after aircraft take-off. Spoilers are provided on the ram wing for stabilization of the ram wing during rotation.

Abstract: Process of landing an airplane on a solid landing surface covered with a layer of water comprising the steps of forming and maintaining a curtain of gas from a point forward and outboard of each of the landing wheels of an airplane on each side of the fuselage thereof to a point forward and central of the wheels and thereby displacing the water of the layer of water from the path of those landing wheels on that solid surface and later releasing the water from the curtain of gas at points lateral of each of the landing wheels while moving the gas curtain and airplane forward at a sufficiently high rate of speed to maintain the landing wheels in contact with the dry surface. Structural modifications of conventional cascade type thrust reversers and target type thrust reversers are provided to accomplish the steps of such process.

Abstract: The airplane of the present invention is of the vertical take-off and landing type powered by one or more jet engines which are mounted to provide thrust necessary for horizontal flight, movable panels direct exhaust gases downwardly toward the ground to provide a ground effect for greater safety upon vertical take-off and landing.

Abstract: An aircraft landing gear assembly includes a strut and tire arranged for load-bearing contact with an underlying surface. A weight transfer shoe interposed between the tire and support surface at touchdown and arranged to pivot to a clear position after touchdown cushions the impact between the tire and the support surface to extend the service life of the tire.

Abstract: A shock absorbing mobile adapter is provided with four members in spaced apart relationship and six shock absorbing arms connecting each member to the other three members and forming an irregular tetrahedron.

Abstract: An undercarriage for an aircraft has a safety device which fails under a predetermined breaking load to separate a leg member of the undercarriage from a rigid element of the undercarriage, the rigid element remaining on the aircraft. The aircraft has on the frame thereof a front mounting and a rear mounting for mounting the undercarriage and said undercarriage comprises said leg member and said rigid element which is mounted in and extends between said front and rear mountings and forms an axle about the axis of which the leg member of the undercarriage can be pivoted for raising the lowering the undercarriage.

Abstract: In a landing gear for an airframe mounted on a cushioned strut, an airframe mounted portion is guided along a landing gear portion after the landing gear touches down. Crash attenuation is absorbed by a work absorbing tube secured at one end thereof to the airframe portion in an encircling relation with respect to the airframe portion. A work applying structural fitting is secured to the airframe at the other end of the work absorbing tube and is adapted to engage and work the tube as the airframe moves downward relative to the airframe portion to dissipate energy involved in arresting downward movement of the airframe. Coupling structure between the airframe and the airframe mounted portion is provided to fail at a predetermined load to permit movement of the airframe relative to the airframe portion.