A landing gear for an aircraft comprising a truck support strut, a landing gear retract mechanism coupling the truck support strut to a frame of the aircraft, so that the truck support strut is suspended from the frame by the landing gear retract mechanism, at least one wheel support arm rotatably coupled to the truck support strut, a carrier member coupled to the landing gear retract mechanism and to the truck support strut so that the landing gear retract mechanism drives the carrier member along the truck support strut, and at least one shock absorber, each of the at least one shock absorber being coupled to both a respective one of the at least one wheel support arm and the carrier member so that movement of the carrier member effects rotation of the at least one wheel support arm relative to the truck support strut.

A landing gear for an aircraft comprising a truck support strut, a landing gear retract mechanism coupling the truck support strut to a frame of the aircraft, so that the truck support strut is suspended from the frame by the landing gear retract mechanism, at least one wheel support arm rotatably coupled to the truck support strut, a carrier member coupled to the landing gear retract mechanism and to the truck support strut so that the landing gear retract mechanism drives the carrier member along the truck support strut, and at least one shock absorber, each of the at least one shock absorber being coupled to both a respective one of the at least one wheel support arm and the carrier member so that movement of the carrier member effects rotation of the at least one wheel support arm relative to the truck support strut.

Wing assemblies (100) comprise one or more wing support structures (24), an inboard-most flap (32), one or more flap supports (28) that operatively couple the inboard-most flap (32) to the one or more wing support structures (24), and one or more flap actuators (31) configured to operatively move the inboard-most flap (32) relative to the one or more flap supports (28). The flap support(s) (28) comprise at least an inboard-most inboard-flap support (106), the flap actuator(s) (31) comprise at least an inboard-most inboard-flap actuator (108) that is outboard of the inboard edge (102) of the inboard-most flap (32), and the inboard-most inboard-flap actuator (108) is spaced-away from the inboard-most inboard-flap support (106).

Wing assemblies (100) comprise one or more wing support structures (24), an inboard-most flap (32), one or more flap supports (28) that operatively couple the inboard-most flap (32) to the one or more wing support structures (24), and one or more flap actuators (31) configured to operatively move the inboard-most flap (32) relative to the one or more flap supports (28). The flap support(s) (28) comprise at least an inboard-most inboard-flap support (106), the flap actuator(s) (31) comprise at least an inboard-most inboard-flap actuator (108) that is outboard of the inboard edge (102) of the inboard-most flap (32), and the inboard-most inboard-flap actuator (108) is spaced-away from the inboard-most inboard-flap support (106).

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.

A hybrid actuator, having a central longitudinal axis, may include a housing defining a central cavity. The hybrid actuator may also include a piston disposed within the central cavity, the piston comprising a piston head that divides the central cavity into a pressure chamber and an annular chamber. The piston houses a pump configured to pump fluid through a port defined in the piston head between the annular chamber and the pressure chamber to extend a piston rod of the piston from the central cavity, according to various embodiments.

A hybrid actuator, having a central longitudinal axis, may include a housing defining a central cavity. The hybrid actuator may also include a piston disposed within the central cavity, the piston comprising a piston head that divides the central cavity into a pressure chamber and an annular chamber. The piston houses a pump configured to pump fluid through a port defined in the piston head between the annular chamber and the pressure chamber to extend a piston rod of the piston from the central cavity, according to various embodiments.

A landing gear control lever system including a lever assembly, a locking assembly, and a switch assembly is disclosed herein. The locking assembly is connected to the lever assembly. The locking assembly has a rotary actuator and a Scotch yoke member operably connected to a portion of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member. The locking assembly can further include a locking arm operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator.

A landing gear control lever system including a lever assembly, a locking assembly, and a switch assembly is disclosed herein. The locking assembly is connected to the lever assembly. The locking assembly has a rotary actuator and a Scotch yoke member operably connected to a portion of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member. The locking assembly can further include a locking arm operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator.