8results about How to "Flying fast" patented technology

This utility model discloses an adjustable two-dimensional tail nozzle, belonging to the field of two-dimensional tail nozzle technology; it includes a connected engine and an adapter casing. A servo is provided on one side of the adapter casing. The output side of the adapter casing consists of a rectangular opening formed by two oppositely arranged fixed plates and two oppositely arranged adjusting plates. A power arm is provided at the output end of the servo. The right end of the power arm is connected to two parallel first connecting rods by a pin shaft. The other ends of the two first connecting rods are respectively connected to two second connecting rods. It can be applied to small afterburning turbojet engines to improve the flight speed of UAVs. Its structure is simple. The synchronous opening and closing movement of the adjusting plates is achieved through a single servo drive source, reducing the control difficulty, realizing engine thrust adjustment, reducing the number of structures, and making it lightweight, highly reliable, and low in cost. By setting a support rod on the outside of the adjusting plate, the adjusting plate can be limited. The structure is simple and the use effect is good.

This invention proposes a symmetrically arranged cross-wing unmanned aerial vehicle (UAV) system, relating to the field of UAVs. It includes a fuselage structure, a power module, and a flight control module. The fuselage structure comprises a cylindrical fuselage and four wings symmetrically arranged in a cross pattern around the cylindrical surface of the fuselage; the four wings are arranged in an X-shape or a cross shape. The power module includes motors and propellers. The motors are located at the wingtips, with their output shafts aligned with the fuselage axis and facing the tail of the fuselage. The propellers are connected to the motor output shafts. The flight control module is located inside the fuselage and is used to control the output speed of the four motors. This system combines the advantages of a quadcopter FPV and a fixed-wing UAV, generating lift from the wings while also cruising and sprinting in fixed-wing form. Furthermore, by changing the motor speeds, it can control the pitch, yaw, and roll attitude of the UAV, eliminating the need for separate control surfaces, thus simplifying the structure and reducing costs.

This invention provides an adaptive sampling flight control method and system for pollutants from unmanned aerial vehicles (UAVs), relating to the field of UAV technology. The method includes the following steps: constructing a three-level heterogeneous grid system and establishing the correlation between grids through cross-level data topology mapping; collecting pollutant concentration data and dynamically activating and / or dormant grids of different precision; calculating a three-dimensional concentration gradient vector using a multi-mode gradient reconstruction mechanism, and combining gradient direction identification and dynamic altitude adjustment strategies to trace the core area of ​​pollutants or track the diffusion boundary of pollutants; selecting different interpolation algorithms according to the system load state and generating a pollution concentration field isosurface model based on the moving cube algorithm; constructing a weighted cost map, integrating real-time concentration change information and historical sampling data to generate a spatially weighted cost value, and dividing different priority areas; implementing hierarchical trajectory planning according to the cost value distribution, and configuring differentiated sampling density and flight speed in different priority areas.

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle high-definition video transmission device, which comprises a vehicle body integrally designed in a cuboid shape; the telescopic wings are respectively arranged at four corners of the aircraft body; the high-definition camera is fixedly arranged at the lower end of the machine body through a multidirectional clamping mechanism, the multidirectional clamping mechanism comprises side wing clamping plates, the side wing clamping plates are symmetrically and movably arranged at the lower end of the machine body through a distance adjusting mechanism, every two side wing clamping plates are arranged in a rectangular mode, and sliding blocks are fixedly installed on the side walls of the side wing clamping plates; according to the device, a ratchet locking mechanism of the side wing clamping plate and the distance adjusting mechanism eliminates transverse displacement and prevents a camera from shaking, elastic lifting of the L-shaped clamping plate is matched with a damper of the damping mechanism, more than 85% of vertical impact energy is absorbed, it is ensured that images do not shake, the image quality of high-definition video transmission equipment is clear, and the service life of the high-definition video transmission equipment is prolonged. The utility model has the characteristics of strong practicability and fast adaptation capability.

This invention provides a tube-launched rotor-wing loitering munition and its operating method, comprising a first-stage propulsion device, a deceleration parachute, a second-stage propulsion device, a multi-rotor UAV, a warhead, and a seeker. The beneficial effects of this invention are: The first-stage propulsion device provides initial velocity during launch, enabling rapid deployment. During flight, the first-stage propulsion device can be automatically jettisoned via a mechanism, reducing the weight of the loitering munition and increasing its operational time. The invention also includes a second-stage propulsion device, which further increases the flight speed of the loitering munition, extending its range and compensating for its insufficient operational distance, ensuring the munition quickly reaches a preset altitude and position. For launch-type rotor-wing loitering munitions, by rationally designing the main body structure and the arm extension and retraction structure, the retraction size is significantly reduced, meeting overload requirements and enabling tube-launching of the rotor-wing loitering munition.

The utility model discloses a flapping wing type bionic aircraft, which relates to the technical field of aircrafts and comprises a mounting rack, a flapping wing driving mechanism is fixedly mounted in the mounting rack, the output end of the flapping wing driving mechanism is fixedly connected with wings, a pitching mechanism is movably mounted at the bottom of the mounting rack, and the pitching mechanism is fixedly connected with the flapping wing driving mechanism. The output end of the pitching mechanism is movably provided with a deflection mechanism, the bottom of the deflection mechanism is provided with a flapping wing adjusting mechanism, and the output end of the flapping wing adjusting mechanism is fixedly connected with the bottom of the wing. The flight stability and accuracy of the aircraft are improved, the flight speed of the aircraft is also improved, in addition, the flapping wing driving mechanism is simple in structure and light in weight, the requirement of the flapping wing driving mechanism for the light weight can be met, and the endurance time of the aircraft is prolonged.

The utility model discloses a kind of unmanned aerial vehicle for realizing vertical take-off and attitude control using small turbojet engine, small turbojet engine is installed at wing tip of wing, small turbojet engine is installed at the back of fuselage (or in front of fuselage) two sides;Small turbojet engine is made to produce upward thrust by vertical rotation 90 ° using turbine worm drive mechanism or motor with self-locking holding torque, and unmanned aerial vehicle vertical take-off is realized;Unmanned aerial vehicle has aileron installed at the trailing edge of left and right wing tips, and the differential deflection of aileron makes unmanned aerial vehicle tilt rotation around longitudinal axis, and the direction of thrust of small turbojet engine is deflected using turbine worm drive mechanism, to realize the flight state stabilization and flight attitude control of unmanned aerial vehicle, so that unmanned aerial vehicle has good maneuverability;Horizontal stabilizer and elevator are omitted, vertical stabilizer and rudder are omitted, so as to reduce flight resistance, which is conducive to improving the flight speed and effective load of unmanned aerial vehicle.

The utility model discloses an unmanned plane wing, including wing and power mechanism, and power mechanism includes base, controller, motor seat, motor, propeller and fairing, and the base is connected with the wing, is equipped with the accommodation groove on the base, and the controller is embedded on the accommodation groove, and the base is connected with the motor seat, and the motor is connected on the motor seat, and the motor is electrically connected with the controller, and the propeller includes base, blade and link cover, and the base is connected with the link cover, and surrounds multiple accommodation cavities with the link cover together, and the blade is multiple, and multiple blades are embedded on multiple accommodation cavities one -to -one, and the base is connected with the motor, and the fairing is equipped with multiple notches, and the fairing is fixedly connected with the base, and multiple blades pass through multiple notches one -to -one. The utility model discloses through setting power mechanism on the wing, can effectively reduce the difficulty of the unmanned plane of using the utility model to rise, and improve flight speed, can better match the navigation use of long range or the unmanned plane of the volume of bigger.