13results 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.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a four-axis eight-rotor heavy-load unmanned aerial vehicle which comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a carbon fiber upper clamping plate, a carbon fiber middle clamping plate, an aluminum alloy bottom plate, four carbon tube walls and two foot stools, and battery mounting openings are reserved in the carbon fiber upper clamping plate and the carbon fiber middle clamping plate; the four carbon tube walls are connected between the carbon fiber upper clamping plate and the carbon fiber middle clamping plate through aluminum alloy tube clamps, each aluminum alloy tube clamp comprises a tube arm clamping plate, and the tube arm clamping plates are fixedly connected with the carbon tube walls through bolts. The four-axis eight-rotor coaxial layout is adopted, compared with a traditional heavy-load unmanned aerial vehicle needing six or eight independent vehicle arms, the wheelbase of the unmanned aerial vehicle is remarkably shortened, the overall structure is more compact, and the size of the unmanned aerial vehicle is greatly reduced on the premise that powerful power of the eight rotors is guaranteed through the design; and the device is more convenient to transport and deploy in a complex and narrow working environment.

The application discloses a kind of multi-constraint condition's fixed wing cluster unmanned aerial vehicle hover control method, it is related to unmanned aerial vehicle cluster flight control field, including the following steps: S1, long plane obtains hover parameter by hover instruction and analysis;S2, long plane is calculated by speed limit and is obtained long plane constraint speed range by multi-constraint speed limiting, so that long plane can enter hover and maintain hover state;S3, by the curve distance of wingman calculation, for the instruction value of evaluation roll angle;S4, wingman is constrained by the flight distribution situation and hover parameter that other unmanned aerial vehicle emits, if aircraft is close to long plane, first determine the constraint of nearest tangent circle to avoid the problem that aircraft enters circle after and generates same air line dislocation;S5, after wingman enters hover state, the instruction value of speed is calculated by calculating expected motion position, to control wingman hover process;The application can be autonomously coordinated to reduce the control pressure of formation collision avoidance, formation keeping demand.

The utility model discloses a hand -throwing unmanned plane suitable for standardization batch production relates to unmanned plane technical field. The utility model discloses three -section foldable fuselage, three -section airfoil and three piece tail fin, through three -section modular fuselage and airfoil design, combine folding hinge positioning, lock catch rigid locking and quick -release dowel down -type locking mechanism, realize the quick disassembly of whole machine in 5 minutes, wherein airfoil carbon tube A inserts the automatic pilot electrical connector of conduction, and tail fin carbon tube B inserts synchronous meshing servo arm, and completely exempts manual wiring step, cooperate task cabin standardization interface, and support function module hot plug replacement. The design replaces traditional cementing technology with full bolt connection, reduces production cost, improves the battlefield deployment efficiency, and through double -insurance locking mechanism and carbon pipe enhanced torsional structure, ensures flight stability, satisfies the standardization batch production demand of military individual soldier carrying and emergency investigation.

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 utility model provides a remote control positioning device for an unmanned aerial vehicle, which belongs to the technical field of remote control of the unmanned aerial vehicle, aims to solve the problems of abnormal flight attitude, inaccurate positioning and the like caused by the fact that a key is easily reset due to unskilled operation or negligence of control of an operator, and comprises a remote control device main body, and a display screen is arranged on the rear side of the top end surface of the remote control device main body; the two protection supporting plates are hinged to the left side and the right side of the outer end of the display screen respectively; two ends of the protective support plate are hinged with the remote control device main body through connecting support shafts; the two driving supports are slidably arranged on the outer sides of the left and right end faces of the remote control device body respectively. The opening and closing control mechanism is arranged between the driving bracket and the protective support plate; the reset key is arranged on the front side of the top end face of the remote control device body. The mistaken touch prevention mechanism is arranged on the outer side of the reset key; and the phenomenon that an operator easily presses a reset key due to unskilled control or misoperation is greatly avoided, and smooth task execution of the unmanned aerial vehicle and flight safety of the unmanned aerial vehicle are guaranteed.

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.

The invention relates to the technical field of aircrafts, and provides an environment sensing method and device and an aircraft. The method comprises the following steps: acquiring a current environment image of an aircraft, and performing feature extraction on the current environment image to obtain image features of the current environment image; obtaining the prior distribution of the obstacle, wherein the prior distribution of the obstacle is generated in advance according to the three-dimensional occupied grid sample set; performing aggregation processing on the image features according to prior distribution of obstacles to obtain aggregation features; based on the aggregated feature, a three-dimensional occupancy grid corresponding to the aircraft is predicted, the three-dimensional occupancy grid being used to indicate an obstacle present in a flight environment of the aircraft. The sensing precision and real-time performance of the aircraft in a complex flight environment can be remarkably improved, and the flight stability and safety of the aircraft are effectively guaranteed.

This invention belongs to the field of flight vehicle design technology, specifically relating to a performance testing system and method for large-size flight units. The system includes a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a cooling system, a power distribution device, and a host computer. The positions of the rotor module and drive motor are adjusted via an adjustable platform. The cooling system and power distribution device achieve heat dissipation and power supply for the drive motor. The host computer performs linearity tests, square wave step tests, frequency sweep tests, and thermal balance tests, thereby obtaining the performance parameters and safe operating boundaries of the large-size flight unit under different positions, voltages, and heat dissipation conditions. This invention considers the high voltage and high heat dissipation requirements of large-size flight units, and designs auxiliary systems such as a cooling system and a bidirectional power distribution device, making it more suitable for actual application scenarios of large-size flight units, with smaller testing errors and strong applicability.