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.

An autonomous remote device for deployment in an area, comprising: a mechanism for launching the device airborne from a first of a plurality of locations; a mechanism for navigating the device when airborne to a second of the plurality of locations; and a mechanism for landing the device at the second of the plurality of locations.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

A landing gear for use on an aircraft, the landing gear including a shock strut and an anti-rotation linkage. The shock strut is positioned at least partially within and guided in movement by a guide member coupled to a frame of the aircraft. The shock strut including an outer cylinder that is shaped and sized to engage the guide member where the guide member guides sliding movement of the outer cylinder, and where the outer cylinder is configured so as to be driven in the sliding movement relative to the guide member, and an inner cylinder disposed at least partly within the outer cylinder. The anti-rotation linkage including a connector plate coupled to the outer cylinder of the shock strut, and an anti-rotation link assembly coupled to both the guide member and the connector plate, the anti-rotation link assembly being configured to maintain the shock strut in a fixed rotational orientation relative to the guide member.

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.

Disclosed is a drone. The present invention includes a plurality of propellers creating a lift to prevent inclination and overturn of the drone due to a lift difference generated from uneven ground, a power driving unit providing a rotation power to each of a plurality of the propellers, a ground sensing unit measuring a distance to a first region of the ground and a shape of the first region, and a controller controlling the power driving unit to differentiate rotation ratios of a plurality of the propellers based on the measured distance and shape if receiving an input signal for landing at the first region.

A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot.

A disclosed controller is configured with logic that, when executed, performs actions to extend landing gear of a maglev vehicle. The actions include receiving a height control target value and transitioning between a standby control state and an active control state. The controller maintains the landing gear in a fixed position when the controller is in the standby control state, and the controller controls extension and retraction of the landing gear according to the height control target value when the controller is in the active control state.

Provided is a self-leveling support apparatus for use with a UAV or stationary device such as a table or ladder, the apparatus having multiple leg members, each associated with a hydraulic or pneumatic cylinder; a connection among the hydraulic or pheumatic cylinders such that they share a common reservoir of fluid; a locking mechanism that obstructs free flow of fluid among the cylinders and stabilizes the UAV or stationary device without the need for electronic sensors or control systems.

An aircraft landing gear assembly (112) including a shock absorber strut (114), a bogie (120), a link assembly (124), and a movement detector (132). The shock absorber strut includes an upper and a lower telescoping parts (118, 116), the upper part being connectable to the airframe of an aircraft and the lower part being connected to the bogie such that the bogie may adopt different pitch angles. The link assembly extends between the upper and lower telescoping parts, such that relative movement between the upper and lower telescoping parts causes relative movement between parts of the link assembly. The movement detector is arranged to detect movement of the link assembly relative to the bogie. The movement detector detects movement by sensing a change in linear displacement of, or angle between, one or more members.