Aerial vehicles may be selectively transitioned between a fixed wing flight configuration and a vertical takeoff and landing (VTOL) configuration. In the fixed wing flight configuration, a forward propeller may rotate in a first forward plane, whereas in the VTOL configuration, the forward propeller may be tilted to rotate in a second forward plane. A forward landing arm may extend downward in the VTOL configuration and be configured to be tilted to a stowed position when the aerial vehicle is in the fixed wing flight configuration. The forward landing arm may be coupled to the forward propeller such that tilting of the forward propeller causes corresponding tilting of the forward landing arm. In some examples, a plurality of such landing arms and propellers are tilted during transitioning of the aerial vehicle, such as one or more forward propellers and landing arms and/or one or more aft propellers and landing arms.

Aerial vehicles may be selectively transitioned between a fixed wing flight configuration and a vertical takeoff and landing (VTOL) configuration. In the fixed wing flight configuration, a forward propeller may rotate in a first forward plane, whereas in the VTOL configuration, the forward propeller may be tilted to rotate in a second forward plane. A forward landing arm may extend downward in the VTOL configuration and be configured to be tilted to a stowed position when the aerial vehicle is in the fixed wing flight configuration. The forward landing arm may be coupled to the forward propeller such that tilting of the forward propeller causes corresponding tilting of the forward landing arm. In some examples, a plurality of such landing arms and propellers are tilted during transitioning of the aerial vehicle, such as one or more forward propellers and landing arms and/or one or more aft propellers and landing arms.

A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

Provided is a flight device that can surely perform transformation operations of legs supporting a fuselage base in landing. A flight device 10 includes: a fuselage base 14; a first leg 26 provided on the fuselage base 14 and transformable between a flight state and a landing state; a second leg 27 provided on the fuselage base 14 as a separate body from the first leg 26 and transformable between the flight state and the landing state; a first drive unit 281 and a second drive unit 282 configured to drive transformation operations of the first leg 26 and the second leg 27; and an operation interconnecting mechanism 16 configured to interconnect the first leg 26 and the second leg 27 in terms of operation.

Provided is a flight device that can surely perform transformation operations of legs supporting a fuselage base in landing. A flight device 10 includes: a fuselage base 14; a first leg 26 provided on the fuselage base 14 and transformable between a flight state and a landing state; a second leg 27 provided on the fuselage base 14 as a separate body from the first leg 26 and transformable between the flight state and the landing state; a first drive unit 281 and a second drive unit 282 configured to drive transformation operations of the first leg 26 and the second leg 27; and an operation interconnecting mechanism 16 configured to interconnect the first leg 26 and the second leg 27 in terms of operation.

A system for use with a tripod landing gear assembly of an aircraft may comprise: a tension strut assembly having a tension strut extending from an upper end to a lower end; a drag brace assembly having an upper brace and a lower brace, the upper brace pivotably coupled to the lower brace at a center point, the lower brace rotatably coupled to the lower end of the tension strut; and a jury linkage pivotally coupled to the drag brace assembly at the center point rotatably coupled to a middle portion of the tension strut, the middle portion between the upper end and the lower end.

A lock system for a landing gear assembly may comprise a housing and a hook configured to rotate relative to the housing. A lock pin may be configured to translate into a rotational path of the hook. An electromechanical actuator may be configured to translate the lock pin.

A lock system for a landing gear assembly may comprise a housing and a hook configured to rotate relative to the housing. A lock pin may be configured to translate into a rotational path of the hook. An electromechanical actuator may be configured to translate the lock pin.

An aircraft includes a landing gear having a shock strut, an outer sleeve at least partially surrounding the shock strut, and a shrink mechanism coupled to both the outer sleeve and the shock strut, where the shrink mechanism moves the shock strut relative to the outer sleeve. The shrink mechanism includes a shaft rotatably coupled to the outer sleeve, an anchor arm coupled to the shaft, a shrink arm coupled to the shaft, the shrink arm and the anchor arm being coupled to the shaft so as to rotate as a unit with the shaft about a shaft rotation axis, relative to the outer sleeve, at least 180° when the anchor arm is coupled to the structure within the wing of the aircraft, and a shrink link rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the shock strut.