The present disclosure provides a landing gear assembly for reducing drag on an aircraft. Landing gear assembly may include a proximal joint, a movable leg extending from the proximal joint, and a base attached to a distal end of the leg. The base may be configured to support the electric aircraft on an environmental surface. The landing gear assembly may transition between a deployed landing position and a collapsed flight position when landing and taking off to provide optimal aerodynamics of the aircraft.

A retractable wheel assembly includes arm assemblies, wheels, a retraction arm, and a threaded shaft. The arm assemblies are hingedly attached to a lower frame of a utility vehicle. Each arm assembly comprises a first arm, a second arm, and a third arm hingedly linked there between. Each wheel is connected to the third arm of each arm assembly. The retraction arm is connected to the second arm, and a threaded shaft. The threaded shaft is configured to be actuated rearwardly where the retraction arm is rearwardly pulled causing the second arm to unfold the arm assembly outwardly and deploy the wheels and for motion of the utility vehicle. Then, the threaded shaft is configured to be actuated forwardly where the retraction arm is pushed forward causing the second arm to fold the arm assembly inwardly and fold the wheels and when the utility vehicle is positioned at rest.

A retractable wheel assembly includes arm assemblies, wheels, a retraction arm, and a threaded shaft. The arm assemblies are hingedly attached to a lower frame of a utility vehicle. Each arm assembly comprises a first arm, a second arm, and a third arm hingedly linked there between. Each wheel is connected to the third arm of each arm assembly. The retraction arm is connected to the second arm, and a threaded shaft. The threaded shaft is configured to be actuated rearwardly where the retraction arm is rearwardly pulled causing the second arm to unfold the arm assembly outwardly and deploy the wheels and for motion of the utility vehicle. Then, the threaded shaft is configured to be actuated forwardly where the retraction arm is pushed forward causing the second arm to fold the arm assembly inwardly and fold the wheels and when the utility vehicle is positioned at rest.

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. A central axis of the bearing is perpendicular to the rear side of the rear spar. The forward trunnion support assembly also includes a side load fitting disposed on the rear side of the rear spar. A first end of the side load fitting is coupled to the second vertical support fitting, and a second end of the side load fitting is coupled to the rear spar.

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. A central axis of the bearing is perpendicular to the rear side of the rear spar. The forward trunnion support assembly also includes a side load fitting disposed on the rear side of the rear spar. A first end of the side load fitting is coupled to the second vertical support fitting, and a second end of the side load fitting is coupled to the rear spar.

A landing support assembly to at least partially support an aerial vehicle on a surface may include a strut extendable to a deployed state and retractable to a stowed state during flight. The strut may be configured to pivot with respect to a bracket coupled to the aerial vehicle between the deployed state and the stowed state. The landing support assembly further may include a strut actuator coupled to the strut via a linkage to cause the strut to pivot relative to the bracket. The landing support assembly also may include a foot coupled to an end of the strut remote from the bracket. The foot may be configured to change between a retracted state during flight having a first cross-sectional area and an at least partially splayed state for at least partially supporting the aerial vehicle and having a second cross-sectional area greater than the first cross-sectional area.

A landing support assembly to at least partially support an aerial vehicle on a surface may include a strut extendable to a deployed state and retractable to a stowed state during flight. The strut may be configured to pivot with respect to a bracket coupled to the aerial vehicle between the deployed state and the stowed state. The landing support assembly further may include a strut actuator coupled to the strut via a linkage to cause the strut to pivot relative to the bracket. The landing support assembly also may include a foot coupled to an end of the strut remote from the bracket. The foot may be configured to change between a retracted state during flight having a first cross-sectional area and an at least partially splayed state for at least partially supporting the aerial vehicle and having a second cross-sectional area greater than the first cross-sectional area.

An aircraft assembly having: a first part; a second part, the second part being movably mounted with respect to the first part; an electro-hydraulic actuator coupled between the second part and a first anchor point, the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further includes a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.

An aircraft assembly having: a first part; a second part, the second part being movably mounted with respect to the first part; an electro-hydraulic actuator coupled between the second part and a first anchor point, the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further includes a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.

A truck assembly for aircraft landing gear is provided. The truck assembly includes a hinge connecting a truck beam to a strut of the landing gear. The hinge is configured to allow the truck beam to rotate about the hinge relative to the strut transversely with respect to the length of the truck beam to thereby pivot the truck assembly relative to the strut between a landing position and a stowing position.