An example charging station for an unmanned aerial vehicle (UAV), the charging station generally including a nest and a charging device. The nest includes an upper portion and a lower portion. The upper portion defines an upper opening sized and shaped to receive a landing apparatus of the UAV, and a diameter of the nest reduces from a first diameter at the upper opening to a second diameter at the lower portion. The charging device is mounted in the nest, and includes a first contact pad and a second contact pad. The charging device is configured to apply a voltage differential across the first contact pad and the second contact pad such that the charging station is operable to charge a power supply of the UAV via the landing apparatus.

An aircraft door controller 100 including a receiver 110 configured to receive a command 14 to move an aircraft door between an open position and a closed position relative to a door frame. The aircraft door controller 100 is configured to not store the command 14 when power to move the aircraft door between the open position and the closed position relative to the door frame is unavailable.

A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.

A wheel well fairing for reducing drag on an aircraft fuselage configured with an open wheel well for stowing landing gear of the aircraft. The wheel well fairing includes a Coanda fairing having a convex-shaped lower portion and an upper portion. The upper portion is configured for positioning adjacent an interior vertically-orientated sidewall of the wheel well, and the convex-shaped lower portion has a bottom surface configured to extend substantially parallel to and positioned adjacent with an outer hull surface of the fuselage. The convex-shaped lower portion is curved inwardly within the wheel well between the upper portion and bottom surface. The Coanda fairing is positioned at an aft portion of the wheel well to redirect airflow out of the wheel well in a rearward direction along the bottom hull surface of the fuselage.

A landing gear system includes a landing gear collar and a strut assembly supported by the landing gear collar. The strut assembly includes a piston that is adjustable between a fully extended position and a fully compress position. The landing gear system further includes a rotary encoder and a controller. The rotary encoder rotates in response adjusting the piston and to outputs a data value in response to its rotation. The controller is in signal communication with the rotary encoder and determines a stroke of the piston based on the data value output from the rotary encoder.

An aircraft includes a frame body that includes an attaching unit on an upper portion thereof, that is formed into a frame-shape structure, and that couples an object to a lower portion thereof, the attaching unit being configured to be capable of adjusting a position in an up-down direction of the attaching unit. A main body including a flying mechanism is positioned on an upper portion of the frame body. A control unit controls a position in the up-down direction of the attaching unit such that a flying posture of the object is controlled in accordance with a posture of the flying mechanism.

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C.sub.G) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

A passive lockable strut is presented. The passive lockable strut comprises a first end; a second end; a fluid chamber between and connected to the first end and the second end; and a fluid within the fluid chamber, wherein the fluid is configured to activate the passive lockable strut to place the passive lockable strut in a locked condition in response to a change in an operating condition applied to the passive lockable strut.

According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

A system for landing a mobile platform, such as an Unmanned Aerial Vehicle (“UAV”) and methods for making and using the same. The system can land the UAV by applying a magnetic levitation force upon the UAV and adjusting the applied magnetic levitation force. The system can initiate a landing process to a designated docking station and can guide the UAV to an adjacency of the designated docking station. Once the UAV has entered the adjacency, the magnetic levitation forces can take control of the landing process. During the landing process, certain magnetic sensitive devices installed on the UAV and/or on the designated docking station can be protected by turning them off or by shielding them. The system overcomes disadvantages of currently-available landing systems by restricting a size and weight of the landing arrangements, as well as, avoiding potential damage to the UAV and the designated docking station.