An unmanned aerial vehicle (UAV) includes a UAV body including a first mounting member, a gimbal, and a plurality of stands. The gimbal includes a second mounting member connected to the first mounting member, and a gimbal body connected to the second mounting member. The plurality of stands are fixedly attached to the gimbal body and configured to rotate together with the gimbal body around a yaw axis of the gimbal body.

This disclosure provides an unmanned aerial vehicle, including a central body; a plurality of arms, connected to the central body; a plurality of motor mounting bases, respectively disposed at ends of the plurality of arms away from the central body; a plurality of motors, respectively mounted on the plurality of motor mounting bases; a plurality of propellers, respectively connected to the plurality of motors, wherein the plurality of motors is configured to drive the propellers to rotate; and a plurality of antennas, respectively disposed on the plurality of motor mounting bases, wherein the plurality of propellers is located lower than the plurality of antennas. The unmanned aerial vehicle provided by this disclosure may ensure open space for mounting the antennas, featuring longer flight duration, fewer folding steps, and a higher storage speed.

A retractable landing gear system for a vertical takeoff and landing (VTOL) aircraft includes a rotational strut rotatably coupled to a fuselage of the VTOL aircraft. The rotational strut includes a first end, a second end, and an intermediate portion extending therebetween. A drag strut includes a first end portion pivotally connected to the rotational strut and a second end portion. A locking link includes a first end section pivotally connected relative to the fuselage, a second end section pivotally connected to the drag strut and an intermediate section having a hinge element. A retraction system is operatively connected to the rotational strut and the locking link. The retraction system is operable to pivot the drag strut about a first axis and rotate the rotational strut about a second axis that is distinct from the first axis.

A system for landing and locomoting on a surface of a structure comprises an unmanned aerial vehicle having a plurality of independently controllable thrusters and an undercarriage including a frame with wheels at corners. The undercarriage further includes a plurality of bars pivotally coupled at respective first ends to the frame and coupled at respective second ends to the unmanned aerial vehicle; wherein the unmanned aerial vehicle is operative to differentially activate the plurality of thrusters so as to tilt with respect to the frame of the undercarriage and to cause a net resultant force on the undercarriage to locomote on the surface of the structure.

Embodiments of the present invention relate to the field of aircraft technologies, and provide an unmanned aerial vehicle including an unmanned aerial vehicle body and a landing gear. The landing gear is entirely accommodated in the unmanned aerial vehicle body when being in a folded state. When being folded, the landing gear in the present invention is entirely accommodated in the unmanned aerial vehicle body, and therefore neither causes unnecessary resistance in air nor blocks an aerial photographing field of view in an aerial photographing process of the unmanned aerial vehicle. In addition, when the unmanned aerial vehicle is not in use, the landing gear is accommodated in the unmanned aerial vehicle body, so that the unmanned aerial vehicle is very compact in structure and easy to accommodate and carry.

A system for landing and locomoting on a surface of a structure comprises an unmanned aerial vehicle having a plurality of independently controllable thrusters and an undercarriage including a frame with wheels at corners. The undercarriage further includes a plurality of bars pivotally coupled at respective first ends to the frame and coupled at respective second ends to the unmanned aerial vehicle; wherein the unmanned aerial vehicle is operative to differentially activate the plurality of thrusters so as to tilt with respect to the frame of the undercarriage and to cause a net resultant force on the undercarriage to locomote on the surface of the structure.

A shock strut includes a first piston having a first hollow interior and a second piston having a second hollow interior. The first piston is movably mounted to the second piston. The shock strut additionally includes a housing having a third hollow interior, and the second piston is movably mounted to the housing. In response to application of a force to the shock strut, the first piston is receivable within the second piston during a first stage of compression and together, the first piston and the second piston are receivable within the housing during a second stage of compression.

A retractable landing gear system configured to contour an aircraft fuselage includes a landing wheel having an axle, a wheel rotation strut assembly coupling the landing wheel to the aircraft fuselage and an actuation strut assembly configured to move the wheel rotation strut assembly between various positions including a deployed position and a stowed position. The axle of the landing wheel is pivotably coupled to a distal end of the wheel rotation strut assembly and configured to pivot relative to the wheel rotation strut assembly as the actuation strut assembly moves the wheel rotation strut assembly between the deployed and stowed positions such that the landing wheel generally contours the aircraft fuselage when the wheel rotation strut assembly is in the stowed position.

Disclosed herein is a VTOL tilt-wing aircraft that serves as a 4-6 passenger airliner for scheduled service between city centers and that is optimized for travel distances from 100-500 miles fully loaded with passengers and fuel. The VTOL aircraft solves technical, cost, and time problems inherent in other forms of transportation, including, but not limited to, rail, passenger airlines, and helicopters. The VTOL aircraft (1) takes off and lands like a helicopter, (2) flies fast like a jet, and (3) costs less than or comparable to a helicopter.

There is provided an energy absorbing landing gear system for attachment to a vertical landing apparatus. The energy absorbing landing gear system includes a linear damper assembly, and a load limiter assembly coupled to the linear damper assembly, the load limiter assembly having at least one deformable element to enhance an energy absorption capability. When the energy absorbing landing gear system is attached to the vertical landing apparatus, during a landing phase, the linear damper assembly contacts a landing surface, and a piston assembly of the linear damper assembly moves a first compression distance toward the load limiter assembly, and when the linear damper assembly reaches a maximum compression, the linear damper assembly moves a second compression distance into the load limiter assembly, and the at least one deformable element deforms.