The present disclosure provides an unmanned aerial vehicle (UAV) having a housing containing electronic components required of the UAV and a heat transfer device for cooling heat generated by said electronic components; at least one boom for connecting said housing to at least one propeller. The boom includes one or more inlet located on a first surface of the boom and within an airflow of said at least one propeller; at least one outlet on a second surface of the boom; a hallow channel extending in interior of the boom from said at least one inlet to said at least one outlet, wherein said airflow generated by said at least one propeller passes into said at least one inlet through the hollow channel to said at least one outlet providing cooling for said heat transfer device.

Provided herein are systems and methods for an unmanned aerial vehicle (UAV) to skid and roll along an environmental surface. A rollable UAV includes an airframe assembly, a propulsion system, and a logic device configured to communicate with the propulsion system. The airframe assembly includes a cylindrical rolling guard configured to allow the UAV to roll along an environmental surface in contact with the cylindrical rolling guard. The logic device is configured to determine a rolling orientation for the UAV corresponding to the environmental surface, maneuver the UAV to place the cylindrical rolling guard of the airframe assembly in contact with the environmental surface, and roll the airframe assembly of the UAV along the environmental surface at approximately the determined rolling orientation while the cylindrical rolling guard is in contact with the environmental surface.

Provided herein are systems and methods for an unmanned aerial vehicle (UAV) to skid and roll along an environmental surface. A rollable UAV includes an airframe assembly, a propulsion system, and a logic device configured to communicate with the propulsion system. The airframe assembly includes a cylindrical rolling guard configured to allow the UAV to roll along an environmental surface in contact with the cylindrical rolling guard. The logic device is configured to determine a rolling orientation for the UAV corresponding to the environmental surface, maneuver the UAV to place the cylindrical rolling guard of the airframe assembly in contact with the environmental surface, and roll the airframe assembly of the UAV along the environmental surface at approximately the determined rolling orientation while the cylindrical rolling guard is in contact with the environmental surface.

A hammering test system includes a hammering test device including a target, a flying unit, and a hammering test mechanism configured to conduct a hammering test on a test object, a surveying instrument including a scanner for acquiring point cloud data by scanning with scanning light, and configured to be capable of performing tracking and distance and angle measurements of the target, and an arithmetic processing unit including a point cloud data analyzing unit configured to calculate shape data by analyzing point cloud data acquired by the scanner, and a flight plan calculating unit configured to calculate a flight plan of the hammering test device based on the shape data calculated by the point cloud data analyzing unit, and the surveying instrument tracks the target of the hammering test device and makes distance and angle measurements when the hammering test mechanism conducts a hammering test.

A vertical takeoff and landing (VTOL) UAV having a UAV main body, two rear landing gears and two front landing gears; the two rear landing gears are fixedly connected to both sides of the rear bottom of the UAV main body, respectively; the two front landing gears are rotatably connected to both sides of the front bottom of the UAV main body, respectively. One end of the front landing gear away from the UAV main body is provided with a locating block. Rotating the front landing gear enables the locating block mounted on the front landing gear to get close to or away from the UAV main body.

A drone docking/landing system includes: a docking portion having a shape of any one of a polygonal pyramid, a truncated polygonal pyramid, a cone, and a truncated cone and being capable of docking a drone; and a landing portion mounted at a lower portion of the drone, having a lower portion that is open, into which the docking portion is inserted, and having an empty inner space, wherein the landing portion has a shape of any one of a polygonal pyramid, a truncated polygonal pyramid, a cone, and a truncated cone, wherein the shape corresponds to the shape of the docking portion so that the docking portion is inserted into the landing portion.

An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

Provided is a discharge apparatus for an air vehicle, capable of reducing a loss of discharge pressure from an aerosol container. The discharge apparatus for an air vehicle discharges contents from an aerosol container 10 mounted on an airframe 101 through a nozzle 15. The aerosol container 10 is mounted on an exterior of the airframe 101, and one end of the nozzle 15 is supported by a discharge end part of the aerosol container 10 via a pipe joint 17 that allows the nozzle 15 to rotate so as to be rotatable around at least one rotation axis M.

A telescoping tail assembly for use on an aircraft having a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction, a tailboom slidable along the housing into various positions including an extended position and a retracted position and one or more control surfaces coupled to the tailboom. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.

A tailsitter aircraft includes an airframe, a thrust array attached to the airframe and a flight control system. The thrust array includes propulsion assemblies configured to transition the airframe from a forward flight orientation to a VTOL orientation at a conversion rate for an approach to a target ground location in a forward flight-to-VTOL transition phase. The flight control system implements an adaptive transition system including a transition parameter monitoring module configured to monitor parameters including a ground speed and a distance to the target ground location. The adaptive transition system includes a transition adjustment determination module configured to adjust the conversion rate of the airframe from the forward flight orientation to the VTOL orientation based on the ground speed and the distance to the target ground location such that the airframe is vertically aligned with the target ground location in the VTOL orientation of the forward flight-to-VTOL transition phase.