A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.

A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.

A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.

The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Systems and methods related to landing unmanned aerial vehicles (UAVs) are provided. In one example, a method includes receiving a UAV on a surface of a landing platform. The method may further include operating a positioning device disposed under the surface to locate the UAV. The method may further include operating the positioning device to move the UAV to a location and/or an orientation on the surface. The UAV may comprise landing gear having a plurality of legs, where each leg comprises a shock absorption system. The method may further include operating the shock absorption system during the receiving operation to reduce force received at stress areas of the UAV, and after the receiving operation, operating the shock absorption system to dampen movement by the UAV. Related devices and systems are also provided.

Systems and methods related to landing unmanned aerial vehicles (UAVs) are provided. In one example, a method includes receiving a UAV on a surface of a landing platform. The method may further include operating a positioning device disposed under the surface to locate the UAV. The method may further include operating the positioning device to move the UAV to a location and/or an orientation on the surface. The UAV may comprise landing gear having a plurality of legs, where each leg comprises a shock absorption system. The method may further include operating the shock absorption system during the receiving operation to reduce force received at stress areas of the UAV, and after the receiving operation, operating the shock absorption system to dampen movement by the UAV. Related devices and systems are also provided.

The present disclosure relates to a leaf spring type landing gear mounted on a lower portion of a fuselage of an aircraft, and more particularly, to a leaf spring type landing gear having improved performance for mitigation and absorption of shocks, including: a first frame connected to the fuselage and bent to have a circle center below; a second frame connected to the first frame; and a third frame connected to the second frame and at least partially bent to have a circle center below, wherein the second frame includes a 2-1st frame and a 2-2nd frame having circle centers formed in opposite directions and is formed to be bent in an S shape.