7results about How to "Ensure flight stability" patented technology

This invention relates to a portable foldable tandem wing aircraft, comprising a frame, a front wing, an arm, a rear wing, a battery pack, a linear motor, a chuck, a mounting base, a first sliding plate, a first spring, a chuck return spring, a second spring, a second sliding plate, arm-wing connectors, a self-locking structure, and a double-ball-joint connecting rod. The mounting base and chuck are located in the middle of the battery pack. The chuck is connected to the output shaft of the linear motor, and the chuck return spring is connected to the mounting base and the chuck. The first sliding plate is slidably mounted on the front end of the battery pack, and the first spring is connected to the first sliding plate. The sliding plate is connected to the fixed base; the second sliding plate is slidably mounted at the rear end of the battery cylinder, and the second spring is connected to the second sliding plate and the battery cylinder; the arm wing connector is located at the front end of the battery cylinder, and the upper and lower ends of the arm wing connector are respectively connected to the arm, the head of the arm is rotatably connected to the arm wing connector, and is rotatably connected to the first sliding plate through a self-locking structure; the left and right sides of the arm wing connector are rotatably connected to the front wing, and the two sides at the rear end of the battery cylinder are rotatably connected to the rear wing; in the folded state, the arm and the rear wing are both locked together with the chuck. This aircraft is not only easy to carry, but also improves the stability during flight.

This utility model discloses an irregularly shaped foldable three-axis drone frame and drone device, comprising: an assembly frame structure; a front rotor assembly structure, comprising two sets, the two sets of front rotor assembly structures being respectively and positionably interchangeably mounted on the front two sides of the assembly frame structure, and the rotation directions of the driving rotation ends of the two sets of front rotor assembly structures being opposite to each other; and a rear rotor assembly structure, comprising a single set, extending to the rear of the assembly frame structure, the rear rotor assembly structure having two sets of coaxially arranged driving rotation ends, the two sets of driving rotation ends being opposite to each other. This solves the technical problem in the prior art where drone frames struggle to simultaneously achieve portability and field of view advantages.

This utility model discloses a drop arrow for killing wild boars using a drone, relating to the field of drone accessory technology. The utility model includes an arrow shaft with an arrowhead on one side and fletching on the other side. A fixing component is provided on one side of the arrow shaft, including a mounting post installed on the side of the arrowhead. This utility model significantly improves the flexibility and adaptability of the drop arrow through modular design. The detachable connection structure between the arrow shaft and the arrowhead allows for quick replacement of the arrowhead or adjustment of the counterweight, thereby precisely adjusting the striking force for wild boars of different sizes. The counterweight is fitted onto the surface of the arrow shaft, and the weight can be increased or decreased according to actual needs, avoiding the drawback of traditional one-piece drop arrows that require complete replacement. The design of the fixing sleeve and the fletching ensures flight stability, while the interlocking structure of the square groove and the square post further prevents fletching deviation, ensuring the drop arrow maintains a precise trajectory after deployment and effectively improving the hunting success rate.

The application relates to the technical field of building measurement construction, in particular to an equipment and a measurement method for automatically measuring prefabricated components based on a space scanning technology, which comprises a unmanned aerial vehicle, a measurement scanning equipment, a balance connecting mechanism and an auxiliary assembly; the unmanned aerial vehicle and the measurement scanning equipment are fixedly connected through the balance connecting mechanism, and the balance connecting mechanism guarantees the balance stability of the measurement scanning equipment during measurement work; through the cooperation of the unmanned aerial vehicle, the measurement scanning equipment and the balance connecting mechanism, the vibration generated in the balance state of the unmanned aerial vehicle in the air scanning work has a positive influence on the accuracy of the scanning work; the unmanned aerial vehicle and the measurement scanning equipment have a buffer stability protection function, and the stability of the connection between the two can be guaranteed in the continuous flight process; the equipment has corresponding work flexibility and improves the scanning work quality.

This invention relates to the field of fuel cell technology and discloses a fuel cell heat dissipation system and control method for active balancing heat dissipation in unmanned aerial vehicles (UAVs). The fuel cell heat dissipation system includes a UAV heat dissipation assembly and an active balancing control subsystem. The UAV heat dissipation assembly includes a liquid cooling circuit and rotors disposed at the tips of multiple heat dissipation arms. The liquid cooling circuit includes coolant channels disposed inside the multiple heat dissipation arms. The coolant channels include in-arm liquid inflow pipes and in-arm liquid return pipes. Multiple in-arm liquid inflow pipes are arranged close to the inner side of the heat dissipation arms, and the multiple inflow pipes converge at the tips of the heat dissipation arms and connect to the in-arm liquid return pipes. The inflow pipes have an S-shaped variable diameter pipe structure, and their arrangement density gradually decreases from the root to the tip of the heat dissipation arm. The active balancing control subsystem includes a sensor group, an actuator group, and a controller. This invention can improve the reliability and flight safety of the UAV thermal management system.

The utility model discloses an adjustable unmanned aerial vehicle load hanger belongs to unmanned aerial vehicle load mounting technical field, including fixed plate, adjusting mechanism, slide rail subassembly, load support and drive mechanism, and the fixed plate top surface is installed with the paired drive mechanism, and the both ends of fixed plate bottom surface are installed with the paired slide rail subassembly, and the adjusting mechanism is set up in pairs, and is installed in the fixed plate bottom surface, and one drive mechanism is connected with the one end transmission of each adjusting mechanism, and the other end of adjusting mechanism is connected on a slide rail subassembly, and the load support is set up in pairs, and both ends are installed on two adjusting mechanisms, and the paired load support is arranged in parallel between adjusting mechanism. The existing unmanned aerial vehicle hanger because specially for specific load custom, lead to when the load replacement needs to be re-customized, increase cost, reduce efficiency's problem is solved, has reduced the cost and time required for load replacement, and ensures the flight stability when mounting different loads.

The application relates to the technical field of unmanned aerial vehicles, and provides an unmanned aerial vehicle control method and device and electronic equipment. The method comprises the following steps: acquiring visual perception information and flight state parameters of an unmanned aerial vehicle; obtaining flight action parameters of the unmanned aerial vehicle at each decision moment by a trained reinforcement learning model according to the visual perception information and the flight state parameters; performing flight control evaluation on a target object according to the visual perception information to obtain flight control credibility of the target object; performing second-order smoothing constraint on the flight action parameters in the case that the flight control credibility meets preset credibility; and determining a flight control instruction for controlling the unmanned aerial vehicle according to the flight action parameters after the second-order smoothing constraint. The application can improve the control accuracy of the unmanned aerial vehicle in a complex environment scene and improve the flight stability of the unmanned aerial vehicle.