A heavy-lift UAV frame includes a central frame portion and a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom hinges are interposed between each of the corner members pivot a boom arm between an extended position for flight and a retracted position for storage and transport. Each boom arm and hinge combination includes a complementary dimension to one side of the central frame portion to position a boom arm parallel thereto when in the retracted position. A plurality of landing gear hinges are positioned along the bottom of the frame and transition a plurality of landing gear legs between a ready for flight position and a storage position. In the storage position each of the legs are positioned diagonally beneath the central frame portion.

An energy absorbing landing system for an aircraft having a fuselage includes landing legs rotatably coupled to the fuselage configured to outwardly rotate when receiving a landing load having a magnitude. The energy absorbing landing system also includes an energy absorption unit coupled to the fuselage and cables coupling the energy absorption unit to the landing legs. The energy absorption unit is configured to selectively apply a resistance to the outward rotation of the landing legs via the cables based on the magnitude of the landing load, thereby absorbing the landing load when the aircraft lands.

An energy absorbing landing system for an aircraft having a fuselage includes landing legs rotatably coupled to the fuselage configured to outwardly rotate when receiving a landing load having a magnitude. The energy absorbing landing system also includes an energy absorption unit coupled to the fuselage and cables coupling the energy absorption unit to the landing legs. The energy absorption unit is configured to selectively apply a resistance to the outward rotation of the landing legs via the cables based on the magnitude of the landing load, thereby absorbing the landing load when the aircraft lands.

An aircraft landing gear assembly is disclosed including a landing gear bracket, a fore lever receiving a fore aircraft wheel, an aft lever receiving a rear aircraft wheel, the fore and aft levers being independently moveable, wherein the bracket further comprises a fore lever stop to prevent downwards movement of the fore lever past a lowest rotational position with respect to the bracket at a first angle α.sub.1 forward from the notional bracket axis, and a rear lever stop to prevent downwards movement of the rear lever past a lowest rotational position at a second angle α.sub.2 behind from the notional bracket axis, wherein the first angle is greater than the second angle. An aircraft and a method of landing an aircraft are also disclosed.

A shock strut assembly for a landing gear may comprise a strut cylinder, a strut piston configured to telescope relative to the strut cylinder, and a locking system. The locking system may be configured to restrict rotation of the strut piston relative to the strut cylinder in response to compression of the shock strut assembly.

A shock strut assembly for a landing gear may comprise a strut cylinder, a strut piston configured to telescope relative to the strut cylinder, and a locking system. The locking system may be configured to restrict rotation of the strut piston relative to the strut cylinder in response to compression of the shock strut assembly.

A skidding phase shock absorber and protection device to protect a part on an aircraft for example at the level of a fuel tank of the aircraft includes a support and a convex plate to assume a first position and a second position and to in the first position, because of the action of compression forces, undergo resisted plastic deformation via an elastic element and in a second position to withstand friction, the device assuring, during a crash landing of the aircraft with an impact phase followed by a skidding phase, both protection against the compression forces generated during the impact phase, via the plastic deformation and the elastic shock absorption, and mechanical protection and protection against heating during the skidding phase.

A system for rolling landing gear includes a skid component attached to an aircraft, wherein the skid component further comprises a first skid tube oriented laterally to a longitudinal axis of the axis, a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube, a first wheel journaled on a first rotational fulcrum, a second wheel journaled on a second rotational fulcrum, a first biasing means attaching the first rotational fulcrum to the first skid tube, and a second biasing means attaching the second rotational fulcrum to the second skid tube, wherein the first biasing means and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and second skid tube.

A system for rolling landing gear includes a skid component attached to an aircraft, wherein the skid component further comprises a first skid tube oriented laterally to a longitudinal axis of the axis, a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube, a first wheel journaled on a first rotational fulcrum, a second wheel journaled on a second rotational fulcrum, a first biasing means attaching the first rotational fulcrum to the first skid tube, and a second biasing means attaching the second rotational fulcrum to the second skid tube, wherein the first biasing means and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and second skid tube.

A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.