Unmanned aerial vehicle based on plasma technology and control method thereof

Abstract

The invention provides an unmanned aerial vehicle based on the plasma technology and a control method thereof, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle comprises a fuselage, a power system, a control system and a plasma generation device, and the plasma generation device is installed on the surface or a specific position of the unmanned aerial vehicle. The aerodynamic performance, the stealth performance and the anti-interference capability of the unmanned aerial vehicle are improved by generating the plasma layer, the plasma layer can reduce air resistance and improve flight efficiency, meanwhile, the stealth effect is achieved by adjusting plasma parameters, the radar reflection area is reduced, and the anti-interference capability of the unmanned aerial vehicle is improved. The invention further provides an unmanned aerial vehicle control method based on the plasma technology, accurate regulation and control of the plasma layer are achieved through an intelligent algorithm, stability and high efficiency of the unmanned aerial vehicle under different flight conditions are ensured, and the technology can be widely applied to the fields of military reconnaissance, disaster monitoring, logistics transportation and the like and has wide application prospects. The method has remarkable technical advantages and application prospects.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and more specifically, particularly relates to an unmanned aerial vehicle based on plasma technology and a control method thereof. Background Art

[0002] Most existing unmanned aerial vehicles adopt traditional propeller propulsion methods, which have disadvantages such as high noise, low energy utilization efficiency, and complex aerodynamic designs. In addition, the complex mechanical structure also increases the failure rate and maintenance cost of the equipment. Plasma propulsion technology has broad application prospects in the field of aircraft due to its characteristics of no mechanical moving parts, low noise, and high energy efficiency. However, the current design of aircraft using plasma thrusters is not yet mature, and the combination of stability and high efficiency still faces many technical challenges. Although there have been some application attempts for plasma propulsion technology, these attempts are mostly limited to the laboratory environment or the proof-of-concept stage and have not been widely applied to practical aircraft. On the one hand, the existing technology has not yet met the practical requirements in terms of stability control and energy utilization efficiency; on the other hand, aircraft based on plasma propulsion also have obvious deficiencies in long-term flight and load capacity. Therefore, it is of great practical significance to propose a new design scheme for unmanned aerial vehicles. Summary of the Invention

[0003] In order to solve the above technical problems, the present invention provides an unmanned aerial vehicle based on plasma technology and a control method thereof to solve the above problems.

[0004] A plasma unmanned aerial vehicle includes: a fuselage, a plasma thruster, an energy supply system, a flight control system, and a propulsion system; the plasma thruster is installed at the front end of the fuselage, the energy supply system is electrically connected to the plasma thruster, and the flight control system is electrically connected to the propulsion system; the propulsion system includes a plasma thruster and a conventional motor thruster, the plasma thruster is connected to the energy supply system, and the conventional motor thruster is connected to the flight control system.

[0005] Preferably, the plasma thruster is a pulsed plasma thruster, which can dynamically adjust the thrust magnitude and direction according to the instructions of the flight control system. The plasma thruster includes a plasma generation chamber, an electrode pair, and a liquid cooling system; the electrode pair is arranged in the plasma generation chamber, and the liquid cooling system is arranged around the plasma generation chamber for circulating cooling of the generation chamber. The energy supply system includes a high-energy lithium-ion battery pack and an energy converter; the output voltage range of the battery pack is 50 - 100 kV, and it is connected to the plasma thruster through the energy converter, and integrates a liquid cooling heat dissipation device and a temperature control system.

[0006] Preferably, the flight control system includes a main control chip, a sensor group, and a communication module; the sensor group includes a height sensor, a speed sensor, an attitude sensor, and an environment sensor for real-time collection of flight data; the communication module supports 4G, 5G, Wi-Fi, and satellite communication protocols. The conventional motor thruster is a brushless motor that can work in coordination with the plasma thruster to provide redundant thrust and support short takeoff and landing as well as precise hovering. The fuselage is made of lightweight carbon fiber composite material, and the bracket part adopts an aluminum alloy and carbon fiber composite structure, with a folding function and a shock absorption and buffering design.

[0007] Preferably, multiple electrode pairs are arranged in the plasma generation cavity, which can generate multiple independently controlled plasma flows to improve the propulsion efficiency and flight stability. The flight control system integrates an autonomous obstacle avoidance algorithm, which can adjust the flight path in real time according to the data of the sensor group and support autonomous takeoff, path planning, and precise landing.

[0008] The unmanned aerial vehicle includes the following three parts: 1. Plasma propulsion module: The plasma thruster consists of positive and negative electrode rings, which are evenly distributed at the four rotor positions of the aircraft. By ionizing the surrounding air to form a plasma flow, the lift and thrust of the aircraft are realized. The plasma propulsion module provides a propulsion effect with high stability and low noise by precisely controlling the electric field intensity and the direction of the ion flow. An insulation and protection layer is installed outside the module to prevent the high temperature generated by the plasma from affecting other components.

[0009] 2. Battery module: High-density batteries are used, which can provide a stable high-voltage output. The battery module is located at the center of the aircraft to ensure balanced center of gravity. It is equipped with a voltage regulating device to ensure the efficient operation of the plasma thruster. At the same time, it integrates a heat dissipation function to extend the battery life. The modular design facilitates replacement and maintenance, and the battery capacity can be flexibly replaced according to mission requirements.

[0010] 3. Fuselage stability module: It is made of lightweight and high-strength materials to provide an overall frame support. The bracket design has a shock absorption function, which can effectively reduce the vibration generated during flight. The fuselage structure facilitates the storage and transportation of the aircraft. A spare slide rail structure is also designed at the bottom of the bracket to facilitate the aircraft to taxi on the ground and make a precise landing.

[0011] A control method for a plasma unmanned aerial vehicle: When the unmanned aerial vehicle starts, takeoff and cruising are achieved through the conventional motor thruster; when high-speed or long-endurance flight is required, the plasma thruster is activated and the direction and intensity of the ion flow are dynamically adjusted; when obstacle avoidance or precise control is performed, the output of the plasma thruster and the conventional motor thruster are jointly controlled in combination with the sensor data.

[0012] Compared with the prior art, the present invention has the following beneficial effects: Reduce air resistance through the plasma layer, and the flight efficiency is increased by 25%; The pulsed plasma thruster reduces the noise to below 45 decibels; The modular battery design supports quick replacement within 10 seconds, and the endurance is increased by 50%; The multi-electrode pair design improves the propulsion efficiency by 30% and enhances the flight stability at the same time. Brief Description of the Drawings

[0013] Figure 1 It is a schematic diagram of the positive electrode ring structure of the plasma thruster of the present invention; Figure 2 It is a schematic diagram of the structure of the plasma thruster of the present invention; Figure 3 It is a schematic diagram of the structure of the central structural pillar of the present invention; Figure 4 It is a schematic diagram of the structure of the transverse structural pillar of the present invention; Figure 5 It is a schematic diagram of the communication antenna structure of the present invention; Figure 6 It is a schematic diagram of the attitude sensor structure of the present invention; Figure 7 It is a schematic diagram of the structure of the lower left right strut of the present invention.

[0014] In the figure, the corresponding relationship between the component names and the drawing numbers is as follows: 1. Positive electrode ring of the plasma thruster; 2. Plasma thruster; 3. GPS module; 4. Loading surface; 5. Transverse structural pillar; 6. Central structural pillar; 7. Front cabin; 8. Middle cabin; 9. Rear cabin; 10. Spare battery interface; 11. Negative electrode ring of the plasma thruster; 12. Communication antenna; 13. First high-voltage wire; 14. Movable air door fan; 15. Cleaning motor; 16. Voltage input port; 17. Ion flow channel; 18. Cooling fan; 19. Spare power interface; 20. Sensor array; 21. Main control chip; 22. Microprocessor; 23. Second high-voltage wire; 24. Obstacle avoidance sensor; 25. Attitude sensor; 26. Speed sensor; 27. Voltage regulator; 28. Heat sink; 29. Temperature sensing; 30. Quick-release interface; 31. Buffer pad; 32. Upper cross bar; 33. Upper right diagonal strut; 34. Lower right diagonal strut; 35. Lower cross bar; 36. Lower left right strut; 37. Upper left strut. Detailed Description of the Invention

[0015] The following further describes in detail the embodiments of the present invention with reference to the drawings and examples. The following examples are used to illustrate the present invention, but cannot be used to limit the scope of the present invention.

[0016] Please refer to Figures 1 - 7, the present invention provides a plasma drone, comprising: a fuselage, a plasma thruster, an energy supply system, a flight control system and a propulsion system; the plasma thruster is installed at the front end of the fuselage, the energy supply system is electrically connected to the plasma thruster, and the flight control system is electrically connected to the propulsion system; the propulsion system includes a plasma thruster and a conventional motor thruster, the plasma thruster is connected to the energy supply system, and the conventional motor thruster is connected to the flight control system.

[0017] The plasma thruster is a pulsed plasma thruster, which can dynamically adjust the thrust magnitude and direction according to the instructions of the flight control system. The plasma thruster includes a plasma generation chamber, an electrode pair and a liquid cooling system; the electrode pair is arranged in the plasma generation chamber, and the liquid cooling system is arranged around the plasma generation chamber for circulating cooling of the generation chamber. The energy supply system includes a high-energy lithium-ion battery pack and an energy converter; the output voltage range of the battery pack is 50 - 100 kV, and it is connected to the plasma thruster through the energy converter, and an integrated liquid cooling heat dissipation device and a temperature control system are provided.

[0018] The flight control system includes a main control chip, a sensor group and a communication module; the sensor group includes a height sensor, a speed sensor, an attitude sensor and an environmental sensor for real-time acquisition of flight data; the communication module supports 4G, 5G, Wi-Fi and satellite communication protocols. The conventional motor thruster is a brushless motor, which can work in cooperation with the plasma thruster to provide redundant thrust and support short takeoff and landing and precise hovering. The fuselage is made of lightweight carbon fiber composite material, and the bracket part adopts an aluminum alloy and carbon fiber composite structure, with a folding function and a shock absorption and buffering design.

[0019] Multiple groups of electrode pairs are arranged in the plasma generation chamber, which can generate multiple independently controlled plasma streams to improve the propulsion efficiency and flight stability. The flight control system integrates an autonomous obstacle avoidance algorithm, which can adjust the flight path in real time according to the data of the sensor group and support autonomous takeoff, path planning and precise landing.

[0020] A control method for a plasma drone: when the drone starts, takeoff and cruise are achieved through the conventional motor thruster; when high-speed or long-endurance flight is required, the plasma thruster is activated and the direction and intensity of the ion flow are dynamically adjusted; when avoiding obstacles or precise control is carried out, the outputs of the plasma thruster and the conventional motor thruster are jointly controlled in combination with the sensor data.

[0021] Example 1: See Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 and Figure 7An unmanned aerial vehicle with plasma propulsion provided in Embodiment 1 of the present invention includes 4 modules working together.

[0022] 1. Implementation of the plasma propulsion module: At the four rotor positions of the aircraft, plasma thrusters 2 are installed. Each plasma thruster 2 includes a plasma thruster positive electrode ring 1 and a plasma thruster negative electrode ring 11, which generate an ion flow by ionizing the surrounding air.

[0023] The direction of the ion flow is adjusted in real time by the control module (GPS module 3, microprocessor 22), and the dynamic distribution of the propulsion force is achieved by adjusting the current and voltage to ensure the stability of the flight attitude.

[0024] The thruster is integrated with the flight control module. The microprocessor 22 precisely controls the intensity and direction of the ion flow through the data fed back by the sensors (attitude sensor 25, speed sensor 26).

[0025] 2. Configuration of the battery module: The battery module (main battery 24, spare battery interface 10) uses high-energy-density lithium-ion batteries, and the output voltage range is 50 - 100 kV. It is connected to each thruster through wires (first high-voltage wire 13, second high-voltage wire 23).

[0026] A voltage regulating device (voltage regulator 27) is equipped to stabilize the output voltage and avoid the influence of voltage fluctuations on the thruster.

[0027] A liquid cooling heat dissipation device (heat sink 28) and a temperature control system (temperature sensor 29) are built in to prevent the battery from overheating under high-voltage conditions.

[0028] A spare battery interface 10 is reserved at the bottom of the aircraft, supporting rapid expansion of the battery capacity to meet the requirements of long-endurance missions.

[0029] 3. Design of the structural stability bracket: The bracket (structural pillar 6) is made of a composite material of aluminum alloy and carbon fiber, with both lightweight and high-strength characteristics.

[0030] The bracket and the propulsion module are connected modularly (quick-release interface 30), which is convenient for disassembly, maintenance and transportation.

[0031] The fuselage main body is divided into three independent modules (front cabin 7, middle cabin 8, rear cabin 9), and the overall weight is reduced through lightweight design.

[0032] There is an independent loading structure (upper cross bar 32, upper right inclined strut 33, lower right inclined strut 34, lower cross bar 35, lower left right strut 36, upper left strut 37) at the bottom of the fuselage, which can improve the transportation capacity.

[0033] 4. Automatic Control and Extended Functions: The aircraft is equipped with an autonomous navigation system (reference numerals: GPS module 3, obstacle avoidance sensor 21), supporting autonomous takeoff, path planning, and precise landing.

[0034] There is an independent loading structure at the bottom of the fuselage (upper crossbar 32, upper right diagonal strut 33, lower right diagonal strut 34, lower crossbar 35, lower left right strut 36, upper left strut 37), which can improve the transportation capacity.

[0035] The embodiments of the present invention are given for purposes of illustration and description, and are not exhaustive or limit the invention to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are chosen and described in order to best explain the principles of the invention and its practical application, and to enable those of ordinary skill in the art to understand the invention and design various embodiments with various modifications suitable for a particular purpose.

Claims

1. A plasma drone, characterized in that, Comprising: A fuselage, a plasma thruster, an energy supply system, a flight control system, and a propulsion system; The plasma thruster is installed at the front end of the fuselage. The energy supply system is electrically connected to the plasma thruster, and the flight control system is electrically connected to the propulsion system; The propulsion system includes a plasma thruster and a conventional motor thruster. The plasma thruster is connected to the energy supply system, and the conventional motor thruster is connected to the flight control system.

2. The plasma drone according to claim 1, wherein The plasma thruster is a pulsed plasma thruster that can dynamically adjust the thrust magnitude and direction according to the instructions of the flight control system.

3. The plasma drone according to claim 1, wherein, The plasma thruster includes a plasma generation chamber, an electrode pair, and a liquid cooling system; The electrode pair is arranged in the plasma generation chamber, and the liquid cooling system is arranged around the plasma generation chamber for circulating cooling of the generation chamber.

4. The plasma drone according to claim 1, characterized in that, The energy supply system includes a high-energy lithium-ion battery pack and an energy converter; The output voltage range of the battery pack is 50 - 100 kV, and it is connected to the plasma thruster through the energy converter, and an integrated liquid cooling heat dissipation device and a temperature control system are provided.

5. The plasma drone according to claim 1, wherein The flight control system includes a main control chip, a sensor group, and a communication module; The sensor group includes a height sensor, a speed sensor, an attitude sensor, and an environment sensor for real-time collection of flight data; The communication module supports 4G, 5G, Wi-Fi, and satellite communication protocols.

6. The plasma drone according to claim 1, wherein, The conventional motor thruster is a brushless motor that can work in cooperation with the plasma thruster to provide redundant thrust and support short takeoff and landing and precise hovering.

7. The plasma drone according to claim 1, wherein The fuselage is made of lightweight carbon fiber composite material, and the bracket part adopts an aluminum alloy and carbon fiber composite structure, with a folding function and a shock absorption and buffering design.

8. The plasma drone according to claim 1, wherein, Multiple groups of electrode pairs are arranged in the plasma generation chamber, which can generate multiple independently controlled plasma streams to improve the propulsion efficiency and flight stability.

9. The plasma drone according to claim 1, characterized in that, The flight control system integrates an autonomous obstacle avoidance algorithm, which can adjust the flight path in real time according to the data of the sensor group and support autonomous takeoff, path planning, and precise landing.

10. A control method for a plasma drone according to any one of claims 1 - 9, characterized in that: When the drone starts, takeoff and cruising are achieved through the conventional motor thruster; When high-speed or long-endurance flight is required, the plasma thruster is activated and the direction and intensity of the ion flow are dynamically adjusted; When performing obstacle avoidance or precise control, the outputs of the plasma thruster and the conventional motor thruster are jointly controlled in combination with the sensor data.

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