A vertical tail of a composite-wing unmanned aerial vehicle (UAV) having a body, a rudder face section, a rotor section, shock absorbing component and a quick installation assembly of circuit. The body includes a tail body frame and a shell. The rudder face section has a rudder machine and a rudder surface. The rudder surface is connected to one end of the tail for steering the directional deflection of the UAV. The shock absorbing component is connected to the lower end plate and the shock absorbing component absorbs the shock to the body. The quick installation assembly of circuit includes a plug, a positioning sleeve and a bias piece, the positioning sleeve is located on the outer circumference of the plug and slidingly connected to the plug, the bias piece is set between the plug and the positioning sleeve, the bias piece can absorb the impact on the plug.

A vertical tail of a composite-wing unmanned aerial vehicle (UAV) having a body, a rudder face section, a rotor section, shock absorbing component and a quick installation assembly of circuit. The body includes a tail body frame and a shell. The rudder face section has a rudder machine and a rudder surface. The rudder surface is connected to one end of the tail for steering the directional deflection of the UAV. The shock absorbing component is connected to the lower end plate and the shock absorbing component absorbs the shock to the body. The quick installation assembly of circuit includes a plug, a positioning sleeve and a bias piece, the positioning sleeve is located on the outer circumference of the plug and slidingly connected to the plug, the bias piece is set between the plug and the positioning sleeve, the bias piece can absorb the impact on the plug.

The present disclosure is directed to controlling, reducing, and/or altering sound generated by an aerial vehicle, such as an unmanned aerial vehicle (UAV), while the aerial vehicle is airborne. For example, one or more transducers, such as piezoelectric thin-film transducers, or carbon nanotube transducers may be applied or incorporated into or on the surface of propeller blades that are used to aerially navigate the aerial vehicle. As the propeller blade rotates and generates sound, the transducers may be activated to generate one or more anti-sounds that cancel, reduce, or otherwise modify the sound generated by the rotation of the propeller blade. The anti-sound combines with the sound and causes interference such that the combined, or net-effect, is an overall cancellation, reduction, or other modification of the sound.

Described herein are unmanned aerial vehicles (UAVs), systems, and methods for capturing panoramic images using cameras onboard a UAV. For example, an embodiment pertains to a UAV including a flight control system, a propulsion system operatively coupled with the flight control system, and an image system comprising navigational cameras and a gimbal camera. The image system is configured to capture a first set of images of a scene using the navigational cameras, stitch the first set of images together to create a first panoramic image of the scene, identify a flight plan for capturing a second set of images with which to create a second panoramic image of the scene using the gimbal camera, capture the second set of images of the scene using the gimbal camera, and stitch the second set of images together to create the second panoramic image.

Described herein are unmanned aerial vehicles (UAVs), systems, and methods for capturing panoramic images using cameras onboard a UAV. For example, an embodiment pertains to a UAV including a flight control system, a propulsion system operatively coupled with the flight control system, and an image system comprising navigational cameras and a gimbal camera. The image system is configured to capture a first set of images of a scene using the navigational cameras, stitch the first set of images together to create a first panoramic image of the scene, identify a flight plan for capturing a second set of images with which to create a second panoramic image of the scene using the gimbal camera, capture the second set of images of the scene using the gimbal camera, and stitch the second set of images together to create the second panoramic image.

A control system includes one or more processors and one or more memories. The one or more memories store one or more computer programs that, when executed by the one or more processors, cause the one or more processors to obtain operation information of a movable platform performing an operation in a target area, determine at least one operation abnormal area of the movable platform performing the operation in the target area according to the operation information, determine a corresponding supplement operation path according to the at least one operation abnormal area, and control the movable flatform to perform a supplement operation based on the supplement operation path.

A control system includes one or more processors and one or more memories. The one or more memories store one or more computer programs that, when executed by the one or more processors, cause the one or more processors to obtain operation information of a movable platform performing an operation in a target area, determine at least one operation abnormal area of the movable platform performing the operation in the target area according to the operation information, determine a corresponding supplement operation path according to the at least one operation abnormal area, and control the movable flatform to perform a supplement operation based on the supplement operation path.

The present invention relates to a parachute deploying apparatus, comprising: a) a manifold with which is releasably coupled a single vessel within which pressurized gas is generated; b) a gas generator which cooperates with said vessel; c) a plurality of hollow tubes which extend obliquely and upwardly from, and are in communication with, said manifold; and d) a plurality of projectiles, each of which formed with a rod that is receivable in a corresponding tube and to each of which is connected a cord that is also connected to a corresponding portion of an undeployed parachute, wherein the pressurized gas which is generated upon triggering of said gas generator is flowable through each of said tubes to propel said plurality of projectiles in different directions and to cause said parachute to become deployed.

The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

A fixed-wing combat aircraft comprising an electrical power source, a propulsion system, a low-power non-propulsion assembly comprising a flight control system, a high-power non-propulsion assembly comprising an electrical weapon system, and a management unit configured to selectively establish on command multiple operating modes comprising: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.