A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. The vertical takeoff and landing aerial vehicle comprises at least one air inlet provided on the top side of a linear support below a lift propeller, and at least one air outlet provided on the linear support. In the vertical takeoff and landing stage of the aerial vehicle provided by the disclosure, airflow generated by rotation of a lift propeller forms a rapid-flowing spatial flow field, which can achieve efficient heat dissipation of a motor and an electronic speed controller in an arm; and in the vertical takeoff and landing unmanned aerial vehicle provided by the utility, the takeoff weight of the unmanned aerial vehicle cannot be increased, power consumption of airborne equipment cannot be increased, and interior space of the arm cannot be occupied.

An energy-load assembly includes an accommodating box, a power source, a load and an undercarriage. The accommodating box can be connected to a body of an unmanned aerial vehicle; the power source is arranged in the accommodating box, and can provide electric energy to the unmanned aerial vehicle; the load is arranged at the bottom of the accommodating box; and the undercarriage is connected to the accommodating box. The energy-load assembly provided integrates the power source, the load and the undercarriage. The corresponding power source and the load can be integrated according to different tasks performed.

An energy-load assembly includes an accommodating box, a power source, a load and an undercarriage. The accommodating box can be connected to a body of an unmanned aerial vehicle; the power source is arranged in the accommodating box, and can provide electric energy to the unmanned aerial vehicle; the load is arranged at the bottom of the accommodating box; and the undercarriage is connected to the accommodating box. The energy-load assembly provided integrates the power source, the load and the undercarriage. The corresponding power source and the load can be integrated according to different tasks performed.

An undercarriage unit is provided. The undercarriage unit comprises: a rotatable wheel; at least one electromagnet for releasably coupling the undercarriage unit to the aircraft; a switch for selectively activating and deactivating the at least one electromagnet; and a controller arranged to actuate the switch. An aircraft having the undercarriage unit is also provided.

A search and rescue drone system includes a buoyant body member, a frame attached to the buoyant body member for carrying a motor and propeller, and an electronic array including a camera, GPS, an EPIRB radio distress beacon, and a transmitter/receiver for remote control flying the drone and communicating with an operator. A laser guidance system may provide coordinates for landing near a swimmer in distress. The search and rescue drone may also be programmed to simply fly to the location of an electronic wearable device, like a bracelet, that is worn by a man overboard. In another embodiment, the search and rescue drone includes pivoting motor mounts, so that it can take off and land vertically with propellers rotating in a horizontal plane, and then the propellers may pivot to rotate in a vertical plane for propulsion across water similar to a fan boat with rescued people aboard.

The present invention discloses an unmanned aerial vehicle including a main body, a plurality of arms, a propulsion assembly and a battery assembly, where each arm is coupled to the main body and the propulsion assembly is disposed on the each arm. The battery assembly is accommodated in a battery compartment of the main body. The battery assembly includes a shell, a battery body substantially disposed in the shell, a clamp button, and a restorable elastic piece. An end of the clamp button is mounted or connects to the shell, and the other end of the clamp button is detachably coupled to the main body. An end of the restorable elastic piece is disposed on the shell or connect to the shell, and the other end of the restorable elastic piece contacts the clamp button.

A drone takeoff and landing system according to an embodiment comprises: a drone including a through-hole; and a landing pad including an extension member which can pass through the through-hole, wherein, when the extension member of the landing pad passes through the through-hole of the drone, an eddy current may occur between the through-hole and the extension member to cause magnetic braking of the drone.

A heavy-lift UAV frame includes a central frame portion and a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom hinges are interposed between each of the corner members pivot a boom arm between an extended position for flight and a retracted position for storage and transport. Each boom arm and hinge combination includes a complementary dimension to one side of the central frame portion to position a boom arm parallel thereto when in the retracted position. A plurality of landing gear hinges are positioned along the bottom of the frame and transition a plurality of landing gear legs between a ready for flight position and a storage position. In the storage position each of the legs are positioned diagonally beneath the central frame portion.

The present invention discloses an unmanned aerial vehicle including a main body, a plurality of arms, a propulsion assembly and a battery assembly, where each arm is coupled to the main body and the propulsion assembly is disposed on the each arm. The battery assembly is accommodated in a battery compartment of the main body. The battery assembly includes a shell, a battery body substantially disposed in the shell, a clamp button, and a restorable elastic piece. An end of the clamp button is mounted or connects to the shell, and the other end of the clamp button is detachably coupled to the main body. An end of the restorable elastic piece is disposed on the shell or connect to the shell, and the other end of the restorable elastic piece contacts the clamp button.

A quick release device 100 for releasably coupling a pair of landing gears in a UAV includes a housing 400 having two slots 102 for receiving landing gears to be locked and released, and two snap levers 200 pivotally mounted in the housing 400 for movement between a lock position and a release position. The snap levers 200 include a locking feature 104 to engage with a corresponding feature on the landing gears to lock them with the housing 400. Snap levers 200 are located such that the two snap levers can be moved together by a single thumb or finger to the released positions. A sheet shaped planar biasing device 300 for biasing snap levers 200 towards the locked position is provided, which includes two generally U-shaped cut-outs defining cantilever springs in contact with the snap levers 200.