5results about How to "Stable flight attitude" patented technology

The application relates to an obstacle-avoiding unmanned aerial vehicle airborne laser radar device and belongs to the technical field of unmanned aerial vehicles. The device comprises a fuselage and a laser radar. Multiple wings are foldably arranged on the outer side of the fuselage. A driving motor is fixed at the outer end of each wing, and the output end of the driving motor is connected with a paddle. A protection mechanism is arranged on the wing and comprises a fixing assembly and a protection ring sleeved with the wing. The protection ring fixes the wing to the fuselage through the fixing assembly. When abnormal power failure occurs, the wing is folded by gravity and drives the protection ring to overturn to protect the paddle. A rack is arranged at the bottom of the fuselage, the laser radar is arranged in the rack, a supporting frame is connected to the rack through a mounting base at the bottom of the rack, and a damping mechanism is arranged on the mounting base and used for landing buffering. The device solves the problems that the folding of the wings of the existing unmanned aerial vehicle depends on manual operation or complex electric control, the landing buffering effect is poor, and the paddles are easily damaged during falling.

The application discloses a kind of based on flight attitude multi pesticide tank unmanned aerial vehicle centroid balance liquid supply control method, obtain unmanned aerial vehicle pitch angle data in flight process, each pesticide tank geometric parameter and liquid state information, according to the change of flight attitude, pesticide tank in liquid free surface form is classified, calculates each pesticide tank liquid centroid coordinate and unmanned aerial vehicle whole machine centroid coordinate. 0-1 mixed linear model is established, under the premise of meeting continuous liquid supply time length constraint, pesticide tank mutual exclusion liquid supply constraint, joint liquid supply amount constraint, liquid supply rate constraint and the liquid amount constraint required by liquid spray system, with the minimum unmanned aerial vehicle whole machine centroid offset of each pesticide tank liquid supply operation as target, dynamically determine the liquid supply state and liquid supply rate of each pesticide tank, realize the collaborative liquid supply control of multi pesticide tank.The application with initiative control and prediction model will instantaneous centroid always be constrained in ideal small range, effectively reduce the centroid deviation of multi pesticide tank unmanned aerial vehicle, improve the flight stability of plant protection unmanned aerial vehicle.

The invention belongs to the technical field of freight unmanned aerial vehicles, and relates to a method for adjusting the center-of-gravity position of a freight unmanned aerial vehicle by utilizing cargos, which comprises the following steps of: when the unmanned aerial vehicle is designed, designing parts with larger weight change at the center-of-gravity position of the unmanned aerial vehicle, designing some counterweights with smaller mass change at the rear part of the unmanned aerial vehicle, and designing a cargo hold at the front part of the unmanned aerial vehicle; the gravity center position of the unmanned aerial vehicle can be conveniently changed according to the cargo position in the cargo filling process, and cargos can be placed at the proper position; gravity sensors are arranged in four directions of the cargo hold of the unmanned aerial vehicle to detect the total mass and mass distribution of the cargo; calculating the ideal position of the center of gravity of the cargo through the total mass of the cargo and the weight information of the unmanned aerial vehicle; comparing information of the actual center-of-gravity position and the ideal center-of-gravity position of the goods to give the direction and distance of the goods needing to move; finally, the goods are fixed after reaching the ideal position, and the goods are prevented from moving in the flying process.

The utility model discloses an unmanned plane soil remote sensing monitoring devices, include: support part, support part includes unmanned plane frame and machine base, machine base is fixed at the bottom of unmanned plane frame, spoiler part, spoiler part includes transverse board, spoiler, inner recess, rotating shaft and drive rod, transverse board is installed at the both sides of machine base outer surface, and inner recess is set up at the one end of transverse board top, and rotating shaft sets up at the both sides of inner recess inner surface, and spoiler rotatoryly connected between two rotating shafts, and drive rod sets up at the outside of one end rotating shaft. The utility model above -mentioned device when practical use, if external is in gale environment, airflow disorder makes unmanned plane flight attitude difficult steady control, and the lateral force and the jounce force that it receives increase greatly, this not only makes flight trajectory deviate predetermined route, also has improved the crash risk significantly, has reduced the stability when unmanned plane flight.

This utility model discloses a 38mm stun-type riot control bullet for riot guns, relating to the field of riot control ammunition technology. The utility model includes a launch tube assembly, the inner cavity of which houses a projectile assembly. The projectile assembly includes a projectile shell disposed inside the launch tube assembly. An end cap is fixedly connected to the bottom of the projectile shell, and a tail fin is fixedly connected to the bottom of the end cap. A flame delay detonator is fixedly connected to the bottom of the inner cavity of the end cap. This utility model reduces air resistance during flight by designing the projectile shell head as a spherical structure with a curvature radius of 15-20mm. Simultaneously, tail fins evenly distributed circumferentially at the bottom of the end cap form an aerodynamic layout similar to a stabilizing wing. The spherical head reduces wind resistance interference, and the tail fins balance attitude shift by generating aerodynamic lift. The combined effect of these two elements makes the projectile's flight attitude more stable, solving the accuracy problem caused by structural design defects in existing products.