Aircraft landing gear forward trunnion support assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side and a forward trunnion support assembly. The forward trunnion support assembly includes first and second vertical support fittings coupled to the rear side of the rear spar, and a trunnion housing with a bearing. The trunnion housing is coupled between the first and second vertical support fittings. The trunnion housing also includes first and second shoulders formed on a top side of the trunnion housing, each of the first and second shoulders having a respective channel formed on a respective top portion thereof. A fuse pin is received within the channels and has a first end extending through the first vertical support fitting and a second end extending through the second vertical support fitting.

A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes an upper cam fastened to the piston and a lower cam fastened to the cylinder. The system further includes a brace configured to be coupled to the shock strut to lock the landing gear in a deployed position, and to fold towards the shock strut during retraction of the landing gear. The system further includes a collar coupled to the brace and the piston and configured to rotate relative to the cylinder in response to folding of the brace such that rotation of the collar rotates the piston and the upper cam relative to the lower cam, the rotation of the upper cam relative to the lower cam forcing the piston towards the aircraft attachment within the cylinder.

A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes an upper cam fastened to the piston and a lower cam fastened to the cylinder. The system further includes a brace configured to be coupled to the shock strut to lock the landing gear in a deployed position, and to fold towards the shock strut during retraction of the landing gear. The system further includes a collar coupled to the brace and the piston and configured to rotate relative to the cylinder in response to folding of the brace such that rotation of the collar rotates the piston and the upper cam relative to the lower cam, the rotation of the upper cam relative to the lower cam forcing the piston towards the aircraft attachment within the cylinder.

Systems and methods for bipedal nose landing gear of an aircraft. One embodiment is a nose landing gear of an aircraft. The nose landing gear includes a shock strut coupled to an axle with a nose wheel, and a folding side brace extending from the shock strut inboard toward a belly of the aircraft and configured to stabilize the shock strut. The nose landing gear also includes a trunnion configured to pivot the shock strut forward toward a nose and inboard toward the belly of the aircraft to retract the nose wheel.

Systems and methods for bipedal nose landing gear of an aircraft. One embodiment is a nose landing gear of an aircraft. The nose landing gear includes a shock strut coupled to an axle with a nose wheel, and a folding side brace extending from the shock strut inboard toward a belly of the aircraft and configured to stabilize the shock strut. The nose landing gear also includes a trunnion configured to pivot the shock strut forward toward a nose and inboard toward the belly of the aircraft to retract the nose wheel.

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

A non jamming shrink latch is provided and may comprise a cradle, a first rocker arm, a first inboard pivot, and a first outboard pivot, wherein the first inboard pivot is coupled to the first rocker arm at a first end and the first outboard pivot is coupled to the first rocker arm at a second end opposite the first end, and wherein the cradle is coupled to the first outboard pivot. In various embodiments, a non jamming shrink latch may further comprise a second rocker arm coupled to the cradle at a second outboard pivot and a second inboard pivot coupled to the second rocker arm opposite the second outboard pivot.

A non jamming shrink latch is provided and may comprise a cradle, a first rocker arm, a first inboard pivot, and a first outboard pivot, wherein the first inboard pivot is coupled to the first rocker arm at a first end and the first outboard pivot is coupled to the first rocker arm at a second end opposite the first end, and wherein the cradle is coupled to the first outboard pivot. In various embodiments, a non jamming shrink latch may further comprise a second rocker arm coupled to the cradle at a second outboard pivot and a second inboard pivot coupled to the second rocker arm opposite the second outboard pivot.

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.