Small supersonic unmanned aerial vehicle capable of dynamically adjusting stability and control method of small supersonic unmanned aerial vehicle

Abstract

The invention discloses a small supersonic unmanned aerial vehicle with dynamically adjusted stability and a control method thereof, and the small supersonic unmanned aerial vehicle comprises a vehicle body, a power system located at the rear part of the vehicle body, an avionics system which is located at the front section of the vehicle body and is provided with an oil supply switch system, and an oil supply system which is located at the middle front part in the vehicle body and is used for providing fuel oil for the power system, the oil supply system comprises a first oil tank, a second oil tank and a third oil tank which are sequentially and independently arranged from front to back. The oil supply switch system comprises an oil supply three-way valve and a partition plate, wherein three ports of the oil supply three-way valve are connected with the first oil tank, the second oil tank and the third oil tank respectively, and the partition plate is located in the oil supply three-way valve and used for opening and closing the ports and enabling the first oil tank and / or the third oil tank to be cut in or cut out for oil supply. The method is used for solving the problems of flight performance and safety caused by severe stability change in the flight envelope of the small supersonic unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to an unmanned aerial vehicle, and particularly to a small supersonic unmanned aerial vehicle with dynamically adjustable stability and a control method thereof. Background Art

[0002] Stability has a great influence on the flight performance and safety of small supersonic unmanned aerial vehicles. Strong stability brings problems in maneuverability. At the same time, a large trim rudder deflection angle will increase the drag of the unmanned aerial vehicle and reduce the flight speed, affecting the flight performance; weak stability or even instability poses high requirements for flight control, affecting the flight quality and flight safety of the unmanned aerial vehicle. The stability of an unmanned aerial vehicle can be understood as being determined by the relative positional relationship between the center of gravity and the aerodynamic center of the unmanned aerial vehicle. When the aerodynamic center of the unmanned aerial vehicle is behind the center of gravity, the unmanned aerial vehicle is stable at this time; and the greater the relative distance, the higher its stability margin, and vice versa, the lower the stability margin; when the aerodynamic center of the unmanned aerial vehicle is in front of the center of gravity, the unmanned aerial vehicle is unstable at this time.

[0003] Typical small supersonic unmanned aerial vehicles mostly use axial flow engines. Therefore, the fuel tank system of the unmanned aerial vehicle, as an important part for balancing the weight of the rear engine, generally has the designed center of gravity of the fuel tank in a position slightly ahead of the center of gravity of the whole aircraft. Therefore, during flight, as the fuel is consumed, the center of gravity of the whole aircraft gradually moves backward. And usually, small supersonic unmanned aerial vehicles are designed with a slender body configuration, with an aspect ratio of more than 10, and the change range of the center of gravity is relatively large. The stability of the unmanned aerial vehicle changes gradually accordingly.

[0004] Typical small supersonic unmanned aerial vehicles use zero-length launch with a booster rocket and parachute recovery. The entire flight mission goes through the process of subsonic (launch) - supersonic (mission) - subsonic (recovery). Therefore, the aerodynamic center of the unmanned aerial vehicle also shows the characteristics of first moving backward (supersonic stage) and then moving forward, which also leads to a large change in the stability of the unmanned aerial vehicle, first increasing and then decreasing; however, in the prior art, it is impossible to dynamically adjust the center of gravity of the unmanned aerial vehicle according to the aerodynamic center of the unmanned aerial vehicle to ensure flight safety. Summary of the Invention

[0005] Object of the Invention: The first object of the present invention is to provide a small supersonic unmanned aerial vehicle with dynamically adjustable stability, which is used to solve the problems of flight performance and safety caused by the drastic change in stability within the flight envelope of the small supersonic unmanned aerial vehicle.

[0006] The second object of the present invention is to provide an adjustment method for a small supersonic unmanned aerial vehicle with dynamically adjustable stability.

[0007] Technical solution: To achieve the above objectives, the small supersonic unmanned aerial vehicle of the present invention includes a fuselage, a power system located at the rear of the fuselage, an avionics system located at the front of the fuselage and equipped with a fuel supply switch system, and a fuel supply system located in the middle front part of the fuselage and used to supply fuel to the power system. The fuel supply system includes a first fuel tank, a second fuel tank, and a third fuel tank that are independently arranged in sequence from front to back. The fuel supply switch system includes a fuel supply three-way valve with three ports respectively connected to the first fuel tank, the second fuel tank, and the third fuel tank, and a partition plate located inside the fuel supply three-way valve and used to open and close the ports and cut the first fuel tank and / or the third fuel tank into or out of the fuel supply.

[0008] Optionally, the fuel supply switch system further includes a drive motor installed on the fuel supply three-way valve and with an output shaft extending into the fuel supply three-way valve. The output shaft of the drive motor is connected to the partition plate, and the drive motor rotates to drive the partition plate to rotate to open and close the ports of the fuel supply three-way valve. The avionics system further includes a control system connected to the drive motor. The control system issues a first instruction to control the drive motor to rotate, driving the partition plate to rotate, and all the ports of the fuel supply three-way valve are conducted. The first fuel tank and the third fuel tank are connected in parallel and then connected in series with the second fuel tank, and then supplied to the engine. The control system issues a second instruction to control the drive motor to rotate, driving the partition plate to rotate, closing the port of the fuel supply three-way valve connected to the third fuel tank, and the first fuel tank and the second fuel tank are connected in series and supplied to the engine. The control system issues a third instruction to control the drive motor to rotate, driving the partition plate to rotate, closing the port of the fuel supply three-way valve connected to the first fuel tank, and the third fuel tank and the second fuel tank are connected in series and supplied to the engine.

[0009] Optionally, the power system includes an engine, an air extraction three-way valve with one port connected to the engine and the other two ports respectively connected to the first fuel tank and the third fuel tank, and a fuel pump with one end connected to the second fuel tank and the other end connected to the engine. Compressed air is led from the engine to the first fuel tank and / or the second fuel tank through the air extraction three-way valve, and the fuel pump sucks fuel from the first fuel tank and / or the third fuel tank into the second fuel tank and supplies it to the engine.

[0010] Optionally, the second fuel tank is connected to the port of the fuel supply three-way valve through an oil inlet pipe, and the second fuel tank is connected to the fuel pump through an oil outlet pipe.

[0011] Optionally, the second fuel tank is located at or near the center of gravity of the unmanned aerial vehicle.

[0012] Optionally, the first fuel tank and the third fuel tank are symmetrically arranged on the front and rear sides of the second fuel tank.

[0013] Optionally, the first fuel tank is connected to the port of the fuel supply three-way valve through a first oil pipe.

[0014] Optionally, the third fuel tank is connected to the port of the fuel supply three-way valve through a third oil pipe.

[0015] Based on the same inventive concept, the present invention discloses a control method for a small supersonic UAV with dynamically adjusted stability, comprising the following steps:

[0016] After the UAV takes off, the control system issues the first command to control the drive motor to rotate, driving the partition plate to rotate. The three ports of the fuel supply three-way valve are all connected. The first fuel tank and the third fuel tank are connected in parallel. Under the suction of the fuel pump and the bleed air boost, fuel is supplied to the second fuel tank at the same flow rate at the same time. The second fuel tank supplies fuel to the engine.

[0017] The avionics system collects the UAV’s flight speed and altitude in real time;

[0018] When the avionics system determines that the drone is entering a supersonic mission, the control system issues a second command, controlling the drive motor to rotate, driving the partition plate to rotate, closing the port on the fuel supply three-way valve connected to the third fuel tank. The first and second fuel tanks are connected in series and then connected for fuel supply. As the fuel is consumed, the center of gravity of the drone gradually shifts backward.

[0019] When the avionics system determines that the drone has ended its supersonic flight and entered the recovery phase, the control system issues a third command to control the drive motor to rotate, driving the partition plate to rotate, closing the port on the fuel supply three-way valve connected to the first fuel tank; the third fuel tank is connected in series with the second fuel tank and connected to the fuel supply; as the fuel is consumed, the center of gravity of the drone gradually moves forward.

[0020] Optionally, the following steps are also included, and the avionics system determines whether the UAV enters a supersonic mission flight by: obtaining the speed of sound at the corresponding flight altitude based on the flight altitude of the UAV; when the flight speed of the UAV is not less than the speed of sound, the UAV enters a supersonic mission flight.

[0021] Beneficial effects: Compared with the existing technology, the present invention has the following significant advantages: the present invention adopts a multi-tank series-parallel fuel supply system design, dynamically adjusts fuel consumption based on the flight mission, matches and achieves the optimal center of gravity change within the full envelope, dynamically adjusts the stability of small supersonic UAVs, and improves flight performance and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the present invention;

[0023] Figure 2 A schematic diagram of the interconnection between the power system, avionics system, and fuel supply system of the present invention;

[0024] Figure 3 This is a schematic diagram of the connection of the first fuel tank in the present invention;

[0025] Figure 4 This is a schematic diagram of the connection of the second fuel tank in the present invention;

[0026] Figure 5 Schematic connection diagram of the third fuel tank in the present invention;

[0027] Figure 6 Schematic connection diagram when the fuel supply switch system of the present invention is in the "1 open" state;

[0028] Figure 7 Schematic connection diagram when the fuel supply switch system of the present invention is in the "simultaneously open" state;

[0029] Figure 8 Schematic connection diagram when the fuel supply switch system of the present invention is in the "3 open" state;

[0030] Figure 9 Schematic diagram of the principle of the control method of the present invention;

[0031] Figure 10 Graph of the change in the center of gravity of the small supersonic unmanned aerial vehicle before and after the present invention adopts the dynamic adjustment method;

[0032] Figure 11 Graph of the change in the stability margin of the small supersonic unmanned aerial vehicle before and after the present invention adopts the dynamic adjustment method. Detailed implementation manners

[0033] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0034] It should be understood that the present invention can be implemented in different forms and should not be construed as being limited to the embodiments presented herein. On the contrary, providing these embodiments will make the disclosure thorough and complete, and will fully convey the scope of the present invention to those skilled in the art. In the drawings, for clarity, the dimensions and relative dimensions of the components may be exaggerated. The same reference numerals denote the same components throughout.

[0035] As Figure 1 and Figure 2 shown, the small supersonic unmanned aerial vehicle in the present invention includes an airframe 1, a power system 2, an avionics system 3, and a fuel supply system 4. Among them, the power system 2 is fixedly installed at the rear position of the airframe 1 to provide the thrust required for the unmanned aerial vehicle during flight; the avionics system 3 is fixedly arranged at the front position of the airframe 1 to provide real-time data acquisition, navigation, and control for the unmanned aerial vehicle; the fuel supply system 4 is fixedly installed at the mid-front position of the unmanned aerial vehicle airframe 1 and is connected to the power system 2 through pipelines to provide fuel for the power system 2. The small supersonic unmanned aerial vehicle has zero-length launch of a booster rocket and parachute recovery, and the flight goes through the subsonic (launch)-supersonic (mission)-subsonic (recovery) process, and can achieve safe subsonic and supersonic flight.

[0036] The avionics system 3 includes a control system 31, a fuel supply switch system 32, and a connecting cable 33. The fuel supply switch system 32 includes a drive motor 321, a partition plate 322, and a fuel supply three-way valve 323. The drive motor 321 is mounted on the fuel supply three-way valve 323, and the output shaft of the drive motor 321 extends into the fuel supply three-way valve 323. The partition plate 322 is connected to the output shaft of the drive motor and is located inside the fuel supply three-way valve 323. The drive motor 321 drives the partition plate 322 to rotate to open and close multiple ports on the fuel supply three-way valve 323. Figure 6 、 Figure 7 and Figure 8 As shown, based on the flight state of the UAV, the control system 31 issues the first instruction, the second instruction and the third instruction. The first instruction can be a same-on instruction, the second instruction is a 1-on instruction, and the third instruction is a 3-on instruction. The control system 31 transmits the instruction to the oil supply switch system 32 via the connecting cable 33. The instruction is executed by the drive motor 321, and the partition plate 322 is adjusted to 3 different positions to realize the adjustment of the oil supply from the oil supply system 4 to the power system 2. The control system 31 issues a first instruction to control the drive motor 321 to rotate, driving the partition plate 322 to rotate, and the three ports of the oil supply three-way valve 323 are all connected. The first fuel tank 41 and the third fuel tank 43 are connected in parallel and then in series with the second fuel tank 42, and then supply the engine 21; the control system 31 issues a second instruction to control the drive motor 321 to rotate, driving the partition plate 322 to rotate, closing the port on the oil supply three-way valve 323 connected to the third fuel tank 43, and the first fuel tank 41 and the second fuel tank 42 are connected in series and then supply the engine 21; the control system 31 issues a third instruction to control the drive motor 321 to rotate, driving the partition plate 322 to rotate, closing the port on the oil supply three-way valve 323 connected to the first fuel tank 41, and the third fuel tank 43 and the second fuel tank 42 are connected in series and then supply the engine 21.

[0037] like Figure 3 、 Figure 4 and Figure 5As shown, the fuel supply system 4 includes a first fuel tank 41, a second fuel tank 42, and a third fuel tank 43. The first fuel tank 41, the second fuel tank 42, and the third fuel tank 43 are independently arranged in sequence from front to back. The second fuel tank 42 is located at or near the center of gravity of the UAV. The first fuel tank 41 and the third fuel tank 43 are symmetrically arranged on the front and rear sides of the second fuel tank 42. The first fuel tank 41 is connected to the port of the fuel supply three-way valve 323 through the first oil pipe 44. The second fuel tank 42 is connected to the port of the fuel supply three-way valve 323 through the fuel inlet pipe 45, and the second fuel tank 42 is connected to the fuel pump 22 through the fuel outlet pipe 46. The third fuel tank 43 is connected to the port of the fuel supply three-way valve 323 through the third oil pipe 47; that is, the three ports of the fuel supply three-way valve 323 are respectively connected to the first fuel tank 41, the second fuel tank 42, and the third fuel tank 43, so that the first fuel tank 41 and the third fuel tank 43 are connected in parallel and then connected in series to the second fuel tank 42 through the fuel supply switch system 32.

[0038] The power system 2 includes an engine 21, a fuel pump 22, and an air bleed three-way valve 23. One port of the air bleed three-way valve 23 is connected to the engine 21, and the other two ports of the air bleed three-way valve 23 are respectively connected to the first fuel tank 41 and the third fuel tank 43. One end of the fuel pump 22 is connected to the second fuel tank 42, and the other end of the fuel pump 22 is connected to the engine 21. When the fuel supply switch system 32 receives the first instruction, compressed air is led from the engine 21 to the first fuel tank 41 and the second fuel tank 43 through the air bleed three-way valve 23, and the fuel pump sucks the fuel from the first fuel tank 41 and the third fuel tank 43 into the second fuel tank 42 to supply the engine 21; when the fuel supply switch system 32 receives the second instruction, compressed air is led from the engine 21 to the first fuel tank 41 through the air bleed three-way valve 23, and the fuel pump sucks the fuel from the first fuel tank 41 into the second fuel tank 42 to supply the engine 21; when the fuel supply switch system 32 receives the third instruction, compressed air is led from the engine 21 to the third fuel tank 43 through the air bleed three-way valve 23, and the fuel pump sucks the fuel from the third fuel tank 43 into the second fuel tank 42 to supply the engine 21. When the power system 2 is working, compressed air is led from the engine 21 to the first fuel tank 41 and the third fuel tank 43 through the air bleed three-way valve 23. When the fuel pump 22 is working, since the pressures in the first fuel tank 41 and the third fuel tank 43 are the same and the diameters of the fuel pipelines are the same, the fuel can be evenly sucked from the first fuel tank 41 and the third fuel tank 43 into the second fuel tank 42 at the same flow rate and finally supplied to the engine 21. By executing the fuel supply switch system 32, the first fuel tank 41 and the third fuel tank 43 can be connected in parallel, and under the suction and air bleed pressurization of the fuel pump 22, they can supply fuel to the second fuel tank 42 at the same flow rate, or the first fuel tank 41 and the third fuel tank 43 can be connected in series with the second fuel tank 42 separately under the suction and air bleed pressurization of the fuel pump 22.

[0039] As Figure 9 、 Figure 10 andFigure 11 As shown, the present invention discloses a control method for a small supersonic UAV with dynamic stability adjustment, comprising the following steps:

[0040] Before the drone takes off, its center of gravity is located in front of the aerodynamic focus as designed, and the drone is in a statically stable state;

[0041] After the drone takes off, the control system issues a first command, and the fuel supply switch system 32 is in the "simultaneously open" state, controlling the drive motor to rotate, driving the partition plate to rotate, and all three ports of the fuel supply three-way valve are connected. The first fuel tank 41 and the third fuel tank 43 are connected in parallel. Under the suction of the fuel pump 22 and the bleed air boost, fuel is simultaneously supplied to the second fuel tank 42 at the same flow rate, and the second fuel tank 42 supplies fuel to the engine 21. Because the second fuel tank 42 has a smaller position deviation from the center of gravity of the drone, the center of gravity of the drone does not change much after fuel consumption, meeting the initial design requirements.

[0042] After 20 minutes of flight, the avionics system 3 collects the UAV’s flight speed V and flight altitude H in real time;

[0043] When the avionics system 3 determines that the UAV has entered a supersonic mission flight, that is, based on the UAV's flight altitude H, the sound speed a at the corresponding flight altitude is obtained. When the UAV's flight speed V is not less than the sound speed a, the UAV enters a supersonic mission flight; when the UAV enters the supersonic stage of flight, the aerodynamic focus moves significantly backward, the distance between the center of gravity and the aerodynamic focus increases significantly, the stability of the UAV increases, and its flight performance decreases; the control system 31 issues a second instruction, the fuel supply switch system 32 is in the "1 open" state, controls the drive motor to rotate, drives the partition plate to rotate, and closes the port on the fuel supply three-way valve connected to the third fuel tank; the first fuel tank 41 and the second fuel tank 42 are connected in series and then connected for fuel supply; as the fuel is consumed, the center of gravity of the UAV gradually moves backward, its stability gradually decreases, and the UAV's flight performance improves;

[0044] When the avionics system 3 determines that the UAV has ended its supersonic flight and is entering the recovery phase, the UAV enters subsonic flight, and the aerodynamic focus moves significantly forward compared to the supersonic phase. The distance between the center of gravity and the aerodynamic focus is significantly reduced, and the stability of the UAV decreases rapidly, resulting in a decrease in its safety. The control system 31 issues a third instruction, and the fuel supply switch system 32 is in the "3 on" state, controlling the drive motor to rotate, driving the partition plate to rotate, and closing the port on the fuel supply three-way valve connected to the first fuel tank. The third fuel tank 43 is connected in series with the second fuel tank 42 to supply fuel. As the fuel is consumed, the center of gravity of the UAV gradually moves forward, its stability gradually increases, and the safety of the UAV is improved. The changes in the center of gravity and stability of the small supersonic UAV before and after the dynamic adjustment method are adopted are shown in the following figure. Figure 10 and Figure 11 shown.

[0045] During flight, the avionics system 3 of the UAV dynamically collects the flight conditions of the UAV. The multi-tank series-parallel fuel supply system design is adopted to dynamically adjust fuel consumption based on the flight mission, match and achieve the optimal center-of-gravity change within the entire flight envelope, dynamically adjust the stability of the small supersonic UAV, and improve flight performance and safety.

[0046] Embodiment

[0047] The maximum takeoff weight of the small supersonic UAV is 150 kg. It uses a zero-length launch of a booster rocket and parachute recovery. The flight altitude is 10,000 m and the flight speed is 350 m / s. The length of the UAV is 5 m, the center of gravity is at 3 m, the weight of fuel tank 1 is 15 kg, the weight of fuel tank 2 is 20 kg, and the weight of fuel tank 3 is 15 kg. After takeoff, the static stability margin of the UAV is 5%, the trim rudder deflection angle of the whole aircraft is 2°, and the additional rudder drag is 2% of the aircraft itself. After continuous flight for 10 minutes, the weight of fuel tank 1 is 10 kg, the weight of fuel tank 2 is 20 kg, and the weight of fuel tank 3 is 10 kg; the center of gravity of the whole aircraft is at 3 m, and 10 kg of fuel is consumed.

[0048] During supersonic flight, due to the rearward movement of the aerodynamic center, the static stability margin of the whole aircraft increases to 30%, the trim rudder deflection angle of the whole aircraft is 5°, and the additional rudder drag is 15% of the aircraft itself; after continuous flight for 5 minutes, the weight of fuel tank 1 is 4 kg, the weight of fuel tank 2 is 20 kg, and the weight of fuel tank 3 is 4 kg, and 12 kg of fuel is consumed; through center-of-gravity optimization adjustment, fuel tank 1 consumes fuel first. After continuous flight for 5 minutes, the weight of fuel tank 1 is 0 kg, the weight of fuel tank 2 is 20 kg, and the weight of fuel tank 3 is 10 kg, and 10 kg of fuel is consumed. The rear static stability margin of the UAV is 20%, the trim rudder deflection angle of the whole aircraft is 3°, and the additional rudder drag is 5% of the aircraft itself; the fuel consumption is reduced by 16.7% within the same time after dynamic adjustment. When the UAV enters the recovery phase, as the mission consumption progresses, the center of gravity of the UAV moves rearward, and the static stability margin drops to -5%. At this time, the UAV becomes statically unstable, which has a greater impact on flight control. To ensure flight safety, it is necessary to control the static stability margin above 5%. Through center-of-gravity optimization adjustment, after the third fuel tank is consumed first, then the second fuel tank is consumed. The center of gravity of the UAV moves forward. As the third fuel tank is consumed, the center of gravity of the UAV returns to the 3 m position, and the static stability margin returns to 5%. From the above analysis, it can be seen that before and after adopting the dynamic adjustment method, the fuel consumption during the supersonic flight stage of the UAV is reduced by 16.7%; at the same time, the static stability margin during the recovery stage returns to 5%, ensuring flight safety.

Claims

1. A small supersonic drone with dynamically adjustable stability, characterized in that: The invention comprises an airframe (1), a power system (2) located at the rear of the airframe, an avionics system (3) located at the front of the airframe and provided with a fuel supply switch system (32), and a fuel supply system (4) located at the middle front of the airframe and used for supplying fuel to the power system (2). The fuel supply system (4) comprises a first fuel tank (41), a second fuel tank (42), and a third fuel tank (43) which are independently arranged in sequence from front to back. The fuel supply switch system (32) comprises a fuel supply three-way valve (323) having three ports respectively connected to the first fuel tank (41), the second fuel tank (42), and the third fuel tank (43), and a partition plate (322) located in the fuel supply three-way valve (323) and used for opening and closing the ports and cutting the first fuel tank and / or the third fuel tank into or out of the fuel supply.

2. The small supersonic drone with stability dynamic adjustment according to claim 1, characterized in that: The oil supply switch system (32) further includes a drive motor (321) installed on the oil supply three-way valve (323) and having an output shaft extending into the oil supply three-way valve (323). The output shaft of the drive motor (321) is connected to the partition plate (322), and the partition plate (322) is driven to rotate to realize the opening and closing of the port of the oil supply three-way valve (323); the avionics system also includes a control system (31) connected to the drive motor (321). The control system (31) issues a first instruction to control the drive motor (321) to rotate, thereby driving the partition plate (322) to rotate. The ports of the oil supply three-way valve (323) are all connected, and the first oil tank (41) and the third oil tank (43) are connected in parallel to the first oil tank (41). The two oil tanks (42) are connected in series and then supply the engine (21); the control system (31) issues a second instruction to control the driving motor (321) to rotate, drive the partition plate (322) to rotate, close the port on the oil supply three-way valve (323) connected to the third oil tank (43), and the first oil tank (41) and the second oil tank (42) are connected in series and then supply the engine (21); the control system (31) issues a third instruction to control the driving motor (321) to rotate, drive the partition plate (322) to rotate, close the port on the oil supply three-way valve (323) connected to the first oil tank (41), and the third oil tank (43) and the second oil tank (42) are connected in series and then supply the engine (21).

3. A small supersonic drone with stability dynamic adjustment according to claim 1, characterized in that: The power system (2) comprises an engine (21), an air induction three-way valve (23) having one end connected to the engine (21) and the other two ends connected to a first fuel tank (41) and a third fuel tank (43), respectively; and a fuel pump (22) having one end connected to the second fuel tank (42) and the other end connected to the engine (21); compressed air is introduced from the engine (21) into the first fuel tank (41) and / or the second fuel tank (43) through the air induction three-way valve (23), and the fuel pump (22) draws fuel from the first fuel tank (41) and / or the third fuel tank (43) into the second fuel tank (42) to supply the fuel to the engine (21).

4. A small supersonic drone with stability dynamic adjustment according to claim 3, characterized in that: The second fuel tank (42) is connected to the port of the fuel supply three-way valve (323) through an fuel inlet pipe (45), and the second fuel tank (42) is connected to the fuel pump (22) through an fuel outlet pipe (46).

5. A small supersonic drone with stability dynamic adjustment according to claim 1, characterized in that: The second fuel tank (42) is located at or near the center of gravity of the drone.

6. A small supersonic drone with stable dynamic adjustment according to claim 1, characterized in that: The first oil tank (41) and the third oil tank (43) are symmetrically arranged on the front and rear sides of the second oil tank (42).

7. A small supersonic drone with stability dynamic adjustment according to claim 1, characterized in that: The first oil tank (41) is connected to a port of the oil supply three-way valve (323) via a first oil pipe (44).

8. A small supersonic drone with stable dynamic adjustment according to claim 1, characterized in that: The third oil tank (43) is connected to a port of the oil supply three-way valve (323) via a third oil pipe (47).

9. A control method for a small supersonic unmanned aerial vehicle with dynamically adjustable stability according to any one of claims 1 to 8, characterized in that, The steps include: After the UAV takes off, the control system issues the first command to control the drive motor to rotate, driving the partition plate to rotate. The three ports of the fuel supply three-way valve are all connected. The first fuel tank and the third fuel tank are connected in parallel. Under the suction of the fuel pump and the bleed air boost, fuel is supplied to the second fuel tank at the same flow rate at the same time. The second fuel tank supplies fuel to the engine. The avionics system collects the UAV’s flight speed and altitude in real time; When the avionics system determines that the drone is entering a supersonic mission, the control system issues a second command, controlling the drive motor to rotate, driving the partition plate to rotate, closing the port on the fuel supply three-way valve connected to the third fuel tank. The first and second fuel tanks are connected in series and then connected for fuel supply. As the fuel is consumed, the center of gravity of the drone gradually shifts backward. When the avionics system determines that the drone has ended its supersonic flight and entered the recovery phase, the control system issues a third command to control the drive motor to rotate, driving the partition plate to rotate, closing the port on the fuel supply three-way valve connected to the first fuel tank; the third fuel tank is connected in series with the second fuel tank and connected to the fuel supply; as the fuel is consumed, the center of gravity of the drone gradually moves forward.

10. The control method of a small supersonic unmanned aerial vehicle with stability dynamic adjustment according to claim 9, characterized in that, The method comprises the following steps, wherein the avionics system determines whether the UAV has entered a supersonic mission flight by obtaining the speed of sound at the corresponding flight altitude according to the UAV's flight altitude, and when the UAV's flight speed is not less than the speed of sound, the UAV enters a supersonic mission flight.

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