CN-122009543-A - Four-rotor low-altitude target interception unmanned aerial vehicle, launching gun and flying method and system

CN122009543ACN 122009543 ACN122009543 ACN 122009543ACN-122009543-A

Abstract

A four-rotor low-altitude target interception unmanned aerial vehicle, a launching gun, a flying method and a system relate to the technical field of unmanned aerial vehicles. The four-rotor low-altitude target interception unmanned aerial vehicle comprises a fuselage, a fixed wing surface assembly, a distributed power system and a flight control module, wherein the fuselage is in large length-diameter ratio and axisymmetric, the fixed wing surface assembly comprises four fixed wings fused with the fuselage, the distributed power system comprises four propellers driven by motors, the flight control module is used for controlling start-stop and flight attitude change, the total resistance coefficient of the fuselage is not more than 1.5, and the pneumatic appearance fused with the fuselage of the four fixed wings meets the normal force coefficient at an attack angle of 10 degrees and is more than 3.2. The four-rotor low-altitude target interception unmanned aerial vehicle has double-mode flight capability, the maximum flight speed can be more than or equal to 300 km/h, the maximum overload capability exceeds 3G, and the four-rotor low-altitude target interception unmanned aerial vehicle is suitable for professional scenes such as black flight of an anti-unmanned aerial vehicle, security anti-terrorism, military light duty tasks and the like.

Inventors

WANG XI
WANG KAILE
ZHANG ZHIYUAN
GUI SHUGUO
LI YIHAI

Assignees

合肥极界无人机科技有限公司

Dates

Publication Date: 20260512
Application Date: 20260317

Claims (10)

1. Four rotor low altitude target interception unmanned aerial vehicle, its characterized in that includes: The machine comprises a machine body, wherein the machine body adopts a machine body with a large length-diameter ratio and extending along a longitudinal axis, the machine body is axisymmetric, and an energy source and a task load are contained in the machine body; The fixed airfoil surface assembly comprises four fixed wings which are fused with the airframe, and is axially symmetrically and fixedly arranged on the side surface of the airframe; The distributed power system comprises four propellers driven by motors, and each motor is arranged in the middle or at the outermost side of the front end of the airfoil of the corresponding fixed wing; the flight control module is used for controlling the start-stop and the flight attitude change of the four-rotor low-altitude target interception unmanned aerial vehicle; The total resistance coefficient of the fuselage is not more than 1.5, the aerodynamic profile of the four fixed wings fused with the fuselage meets the requirement that the normal force coefficient at an attack angle of 10 degrees is more than 3.2, the maximum flying speed of the four-rotor low-altitude target interception unmanned aerial vehicle is more than or equal to 100 km/h, and the maximum overload capacity is more than 2G.
2. The four-rotor low-altitude target-intercepting drone of claim 1, The machine body is integrally formed by carbon fiber, is partially reinforced by an aluminum alloy frame, and/or The center diameter of the machine body is 50-100 mm, the length is 350-500 mm, and/or The fixed wings in the fixed wing surface component are in a trapezoid or triangle structure, the distributed power system is positioned at the wing tip of the fixed wings, a composite wing power fusion technology is adopted, and the tail part of each distributed power system is provided with a guide cone, and/or The motor is a brushless DC motor for driving a 6-8 inch propeller, and/or The flight control module adopts an H743 flight control chip, integrates vision guidance and strapdown guidance technologies, and/or The object detection type of the flight control module supports manual identification and locking of people, unmanned aerial vehicles and vehicles, the minimum object identification size is 36 multiplied by 36 pixels, the anti-shielding duration time is more than or equal to 3s, and/or The flight control module supports ground station control, is capable of receiving ground control instructions to control flight, and/or The four-rotor low-altitude target interception unmanned aerial vehicle further comprises an independent navigation module or a navigation module integrated with the flight control module, and is used for controlling the four-rotor low-altitude target interception unmanned aerial vehicle to conduct guided flight based on navigation targets and/or The turning radius of the four-rotor wing low-altitude target interception unmanned aerial vehicle is within 10 meters.
3. The four-rotor low-altitude target-intercepting drone of claim 2, wherein, The fixed airfoil surface component does not comprise any deflectable pneumatic control surface, and the flying attitude is controlled only by the rotating speeds of four motors, and/or The flight control module is developed based on Betaflight Configurator traversing the ground station, integrates an end AI locking guidance algorithm, can accurately identify, lock and damage the targets in the air and the ground, and/or The four-rotor low-altitude target interception unmanned aerial vehicle and the ground station realize data transmission through a communication frequency band of 2.4 GHz, and the maximum communication distance is 10-20 km when the viewing distance is not blocked, and/or The navigation module is an AI locking guidance module, and can be combined with artificial intelligence to realize autonomous searching of the target and tracking of the target.
4. The four-rotor low-altitude target-intercepting drone of claim 1, The energy source is a rechargeable lithium battery or a nickel-hydrogen battery, adopts a fixed mounting or detachable electricity changing mode, and/or The task load is loaded in a load cabin of the head of the four-rotor low-altitude target interception unmanned aerial vehicle, adopts a standardized interface design, comprises a load power supply module and a load control module, supports 5V/12V dual-voltage output, has a maximum load weight of 500g, can adapt to the loads of ammunition, medical bags and monitoring equipment, and/or The four-rotor low-altitude target interception unmanned aerial vehicle supports a handheld, launching gun launching and ground take-off mode and/or The four-rotor low-altitude target interception unmanned aerial vehicle can realize seamless switching of vertical take-off and landing and high-speed patrol modes.
5. The quad-rotor low-altitude target-intercepting drone of claim 4, The energy source comprises a detachable lithium battery, a factory intelligent charger and a battery management system BMS, and/or The capacity of the lithium battery is 3000-4000 mAh, the voltage is 22.2V, the quick charge mode is supported, the lithium battery can be fully charged within 2 hours through the intelligent charger, and/or The battery management system BMS has the triple protection functions of overcharge, overdischarge and short circuit, and ensures the safety and stability of energy supply.
6. The four-rotor low-altitude target-intercepting drone of claim 1, The four-rotor low-altitude target interception unmanned aerial vehicle meets the flight performance parameters that the maximum flight speed is greater than or equal to 300 km/h, the cruising speed is 80-150 km/h, the endurance time is greater than or equal to 8 minutes, the range is greater than or equal to 6km, the operation height is 50-2000 m, the wind resistance level is less than or equal to 6 levels, the maximum overload capacity exceeds 3G, and/or The four-rotor low-altitude target interception unmanned aerial vehicle is optimized through structural sealing and material selection, the working temperature range is-20 ℃ to 50 ℃, the storage temperature range is-30 ℃ to 30 ℃, the protection grade reaches IP54, the stability under a complex environment reaches 99.2%, and/or The take-off weight of the four-rotor low-altitude target interception unmanned aerial vehicle can be controlled below 2.2 kg, and the single-soldier portable carrying and quick deployment can be realized.
7. A launch gun adapted for a four-rotor low-altitude target-intercepting drone according to any one of claims 1 to 6, comprising: The launching tube is provided with a long tube-shaped cavity for accommodating the four-rotor low-altitude target interception unmanned aerial vehicle according to any one of claims 1 to 6, and a high-pressure gas generating device is arranged at the bottom of the cavity and can generate a large amount of high-pressure gas after activation so as to push the four-rotor low-altitude target interception unmanned aerial vehicle out; The firing device is used for activating the high-pressure gas generating device based on manual triggering of a flight crew or an automatic triggering instruction sent by the four-rotor low-altitude target interception unmanned aerial vehicle under a target locking program.
8. The launch gun of claim 7, further comprising a communication module for communicating with the quad-rotor low-altitude target-intercepting drone as a ground station for flight control or guidance thereof.
9. The flying method for intercepting the unmanned aerial vehicle is characterized by comprising the following steps of: inserting the quad-rotor low-altitude target-intercepting drone of any of claims 1-6 into a cavity of a launch gun; the firing device is triggered by manual triggering of a flying hand or an automatic triggering instruction sent by the four-rotor low-altitude target interception unmanned aerial vehicle under a target locking program, and the four-rotor low-altitude target interception unmanned aerial vehicle is endowed with initial speed through high-pressure gas, so that the four-rotor low-altitude target interception unmanned aerial vehicle is rapidly positioned and started.
10. A system of a four-rotor low-altitude target-intercepting drone comprising a four-rotor low-altitude target-intercepting drone according to any of claims 1-6 and a launch gun according to claim 7 or 8.

Description

Four-rotor low-altitude target interception unmanned aerial vehicle, launching gun and flying method and system Technical Field The invention relates to the technical field of unmanned aerial vehicles, in particular to a four-rotor low-altitude target interception unmanned aerial vehicle, a launching gun, a flying method and a system. Background A Rotary-wing UAV (Rotary-wing UAV) is a type of unmanned aircraft that generates lift by one or more rotating propellers (rotors) to achieve vertical lift, hover, and flexible maneuver. They do not need runway, and can finish take-off, landing and flight tasks in a narrow space. Compared with a fixed wing unmanned aerial vehicle, the rotary wing unmanned aerial vehicle is more flexible, is suitable for various market segments such as industry, agriculture, mapping, logistics and the like, the market scale predicts that the growth rate of the compound year in 2025-2030 is more than 10%, and the market space breaks through 100 hundred million yuan. Along with the rapid development of unmanned aerial vehicle technology, the unmanned aerial vehicle technology is increasingly widely applied to civil, security and military fields, but the performance requirements of different fields on unmanned aerial vehicles are obviously different, the existing unmanned aerial vehicle technology also has great defects, such as heavy portability of civil unmanned aerial vehicles, simplicity and convenience in operation, low speed and weak wind resistance, professional security unmanned aerial vehicles need to have remote monitoring and rapid response capability, but most of existing products have deployment delay, and military unmanned aerial vehicles pursue high speed, accuracy and reliability, but traditional products have large volume, rely on special sites and high cost, and are unfavorable for individual deployment. Particularly, in key scenes such as black flight, border patrol and the like of the anti-unmanned aerial vehicle, extremely high requirements are put on the rapid deployment capability, low-altitude pursuit speed, target locking precision and reliability of the unmanned aerial vehicle. The existing solution has response delay exceeding a few minutes, or has insufficient stability under complex wind conditions, or can not realize accurate interception of a small target, so that the operation efficiency is low and the hidden danger of secondary risk is prominent. Through searching the prior art, the existing unmanned aerial vehicle technology is found to have the following specific problems and defects under key scenes such as black flight, border patrol and the like of the anti-unmanned aerial vehicle: 1. the speed and flexibility contradiction is that the high-speed unmanned aerial vehicle mostly adopts a fixed wing design, needs a special runway, has poor maneuverability, has limited speed (usually less than or equal to 80 km/h) and can not meet the requirement of high-speed pursuit; 2. the deployment efficiency is low, most specialized unmanned aerial vehicles are required to be deployed in a cooperation way by multiple persons, the startup calibration time exceeds 5 minutes, and emergency tasks cannot be dealt with; 3. The load adaptation is single, namely the existing unmanned aerial vehicle load interface is non-standardized, only specific equipment can be adapted, the function expansion is limited, and the use cost is high; 4. the environmental adaptability is insufficient, the wind resistance level is more than or equal to 4 levels, the operation stability is poor under the high and low temperature environment, the protection level is low, and the influence of dust and splash is easy; 5. The tactical suitability is poor, the operation logic is disjointed with the existing military training system, the official and soldier has great hand difficulty, the training period is long, and the combat force is difficult to form rapidly. Thus, there is an urgent need to develop a new tactical unmanned aerial vehicle to address the current drawbacks and deficiencies. Disclosure of Invention Accordingly, the present invention is directed to a four-rotor low-altitude target interception unmanned aerial vehicle, a launching gun, a flying method and a system thereof, so as to at least partially solve the above-mentioned problems. In order to achieve the above object, as a first aspect of the present invention, there is provided a four-rotor low-altitude target interception unmanned aerial vehicle, comprising: The machine comprises a machine body, wherein the machine body adopts a machine body with a large length-diameter ratio and extending along a longitudinal axis, the machine body is axisymmetric, and an energy source and a task load are contained in the machine body; The fixed airfoil surface assembly comprises four fixed wings which are fused with the airframe, and is axially symmetrically and fixedly arranged on the side surface of the airframe; The distributed power syst