Systems and methods for pivoting main landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a trunnion coupled to a bulkhead and configured to pivotally couple the shock strut with the bulkhead. The main landing gear also includes a folding brace extending from the shock strut in a forward direction toward a nose of the aircraft and configured to stabilize the shock strut. The main landing gear further includes a retraction actuator configured to pivot the shock strut about the trunnion to retract the one or more wheels in the forward direction toward the nose and up toward a fuselage of the aircraft.

Systems and methods for pivoting main landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a trunnion coupled to a bulkhead and configured to pivotally couple the shock strut with the bulkhead. The main landing gear also includes a folding brace extending from the shock strut in a forward direction toward a nose of the aircraft and configured to stabilize the shock strut. The main landing gear further includes a retraction actuator configured to pivot the shock strut about the trunnion to retract the one or more wheels in the forward direction toward the nose and up toward a fuselage of the aircraft.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

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 landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

An Unmanned Aerial Vehicle (UAV) according to various embodiments may include: a housing; a motor arranged in an inner space of the housing; a rotor which is rotated by the motor and includes at least one cam structure; and at least one landing member which serves as at least part of the housing and selectively protrudes from the housing depending on interference of the cam structure. An UAV according to various embodiments may include: a housing; at least one rotor blade arranged in an inner space of the housing; and at least one landing member. The at least one landing member may serve as part of the housing in a closed position and protrudes from the housing in an open position such that a load of the UAV can be supported during landing. Other embodiments are also possible.

An Unmanned Aerial Vehicle (UAV) according to various embodiments may include: a housing; a motor arranged in an inner space of the housing; a rotor which is rotated by the motor and includes at least one cam structure; and at least one landing member which serves as at least part of the housing and selectively protrudes from the housing depending on interference of the cam structure. An UAV according to various embodiments may include: a housing; at least one rotor blade arranged in an inner space of the housing; and at least one landing member. The at least one landing member may serve as part of the housing in a closed position and protrudes from the housing in an open position such that a load of the UAV can be supported during landing. Other embodiments are also possible.

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.