Airfoil auxiliary control air-breathing electric propulsion upper atmosphere aircraft

Abstract

The invention relates to the technical field of low-orbit aircrafts, in particular to an airfoil auxiliary control air-breathing electric propulsion upper-layer atmosphere aircraft which comprises a main aircraft body, a deflection folding assembly, an electric driving system and a power supply system. The deflection folding assembly is used for locking the position of the folding wing folded on the main wing before the aircraft takes off, and is used for actively unlocking the main wing to unfold the folding wing and locking the position of the unfolded folding wing after the aircraft enters an orbit; when the folding wings of the aircraft are in the unfolded state, the folding wings are driven to deflect so as to adjust the deflection angles of the folding wings relative to the surfaces of the main wings; the power supply system is used for supplying power to the electric driving system and the deflection folding assembly. According to the device, the folding wings are folded to reduce the size of the whole aircraft, so that the requirement on the space size of the carrier is reduced; the aerodynamic lift-drag ratio of the aircraft is adjusted by adjusting the deflection angle of the folding wings, and then aerodynamic force control capacity is provided for the aircraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of low-orbit aircraft, in particular to a wing-surface auxiliary control air-breathing electric propulsion upper atmosphere aircraft. BACKGROUND

[0002] The upper atmosphere aircraft refers to an aircraft flying in the upper atmosphere space (86-600km). Due to the significant influence of aerodynamic force, the aircraft has the characteristics of aerospace integration. In order to maintain long-term on-orbit flight, power needs to be used for orbit maneuvering or maintaining.

[0003] Conventional aircraft uses chemical propulsion or electric propulsion, resulting in the need for the aircraft to carry more propellants. The current upper atmosphere aircraft mainly has the following two problems: 1. The aircraft can only rely on momentum exchange devices for orbit change or attitude adjustment. When the momentum exchange device is saturated, direct force is needed for unloading, which not only increases the weight of the aircraft, but also limits the on-orbit life of the aircraft; 2. The existing upper atmosphere aircraft uses an electric propulsion system with a working medium, which cannot effectively utilize the gas in the external environment to achieve in-situ utilization of the working medium.

[0004] Therefore, it is necessary to provide a wing-surface auxiliary control air-breathing electric propulsion upper atmosphere aircraft to solve the above problems. SUMMARY

[0005] The present application provides a wing-surface auxiliary control air-breathing electric propulsion upper atmosphere aircraft to solve the existing problems.

[0006] The wing-surface auxiliary control air-breathing electric propulsion upper atmosphere aircraft of the present application adopts the following technical scheme, comprising: A main body, opposite sides of which are provided with main wings, and a head portion of the main body is provided with an air intake system; A deflection and folding assembly is arranged on the main wing, and an output end of the deflection and folding assembly is connected with a folding wing. The deflection and folding assembly is used to lock the position of the folding wing folded on the main wing before the aircraft takes off, to actively unlock the main wing after the aircraft enters the orbit to make the folding wing unfold and lock the position of the unfolded folding wing, and to drive the folding wing to deflect to adjust the deflection angle of the folding wing relative to the surface of the main wing when the folding wing of the aircraft is in the unfolded state; An electric drive system is arranged at the tail portion of the main body, and a working medium inlet of the electric drive system is in communication with the outlet of the air intake system; A power supply system is arranged for supplying power to the electric drive system and the deflection and folding assembly. The air intake system is used to capture the thin nitrogen and oxygen in the super low orbit environment and compress the nitrogen and oxygen as the working medium source of the electric drive system. The electric drive system is used to store, ionize and accelerate the inhaled working medium to be sprayed out and generate thrust to maintain the power of the aircraft orbit flight.

[0007] The further technical scheme of the present application, the deflection folding assembly comprises: The deflection assembly comprises: a rudder fixed to the bottom of the main wing, the output end of the rudder is connected with a deflection shaft, the end of the deflection shaft is provided with a connecting frame, the connecting frame is connected with the folding wing through a hinge structure; the rudder drives the connecting frame to drive the folding wing to deflect through the deflection shaft, so as to adjust the deflection angle of the folding wing relative to the surface of the main wing; And the folding assembly comprises: a torsion spring and a locking assembly arranged on the hinge structure, the locking assembly is used for locking the folding wing when the folding wing is folded on the main wing through the hinge structure, and the locking assembly is used for actively unlocking the folding wing after the aircraft enters the orbit, so that the folding wing is unfolded under the torsion of the torsion spring and the position of the folding wing is locked.

[0008] The further technical scheme of the present application, the hinge structure comprises: Female hinge; Male hinge, which is connected with the female hinge through a pin shaft; Wherein, the free end of the female hinge is connected with the connecting frame, the free end of the male hinge is connected with the folding wing, the torsion spring is sleeved on the pin shaft, and one free end of the torsion spring is connected with the female hinge on the main wing, and the other free end of the torsion spring is connected with the male hinge on the folding wing.

[0009] The further technical scheme of the present application, the locking assembly comprises: The electromagnetic ejector is arranged on the male hinge; and the end face of the female hinge is provided with a pin hole; the elastic ejector of the output end of the electromagnetic ejector corresponds to the pin hole when the folding wing is unfolded; Wherein, the female hinge and the male hinge are made of electromagnetic material, when the folding wing is folded on the main wing around the hinge structure, the male hinge and the female hinge are powered on, the magnetic connection between the male hinge and the female hinge is generated to realize the folding position locking of the folding wing; after the aircraft enters the orbit, the power supply of the male hinge and the female hinge is controlled to be disconnected, the folding wing is unfolded around the hinge structure under the torsion of the torsion spring, and the elastic ejector of the electromagnetic ejector is driven to insert the elastic ejector into the pin hole, so as to lock the unfolded position of the folding wing.

[0010] The further technical scheme of the present application, the air inlet system comprises an air inlet channel, the air inlet channel is arranged inside the main body along the length direction of the main body, the inlet of the air inlet channel faces the head of the main body, the outlet of the air inlet channel faces the tail of the main body, and the outlet of the air inlet channel and the working medium inlet of the electric drive system are communicated.

[0011] The further technical scheme of the application, the air inlet channel comprises: an air suction contraction section, the outlet of the air suction contraction section is connected with a straight line conveying section, the outlet of the straight line conveying section is communicated with the inlet of the electric driving system, wherein, the air suction contraction section is used for collecting the rarefied nitrogen and oxygen gas in the ultra-low orbit environment, compressing the nitrogen and oxygen gas and accelerating the conveying of the nitrogen and oxygen gas to the straight line conveying section, the straight line conveying section is used for conveying the compressed working medium to the electric driving system, and the electric driving system is used for ionizing the working medium entering the straight line conveying section and inputting to accelerate the ejection to generate thrust.

[0012] The further technical scheme of the application, the electric driving system adopts an electric thruster, the working medium inlet of the electric thruster is communicated with the outlet of the straight line conveying section, and the electric thruster is used for ionizing the working medium entering the straight line conveying section and inputting to accelerate the ejection to generate thrust.

[0013] The further technical scheme of the application, the power supply system comprises a plurality of solar cell panels, the plurality of solar cell panels are arranged on the surfaces of the folding wing, the main wing and the main body, the solar cell panels are used for converting solar energy into electric energy and storing the electric energy in the battery, and the battery is used for supplying power for the electric driving system, the rudder of the deflection folding assembly, the female hinge, the male hinge and the electromagnetic spring pin of the aircraft.

[0014] The beneficial effects of the application are: 1. The aircraft of the application generates a certain aerodynamic force by designing the deflection folding wing, forming a control moment, and then assisting in adjusting the attitude of the aircraft. In addition, the aircraft is designed with an air inlet channel to capture external atmospheric molecules to provide the electric propulsion system, thereby reducing the consumption of the working medium of the aircraft. When the aircraft is launched, the folding wing of the aircraft is folded to reduce the size of the entire aircraft, thereby reducing the requirement for the space size of the carrier. In the working phase of the aircraft, the folding wing is unfolded and the deflection angle of the folding wing is adjusted to adjust the lift-drag ratio of the aircraft, thereby providing the aircraft with aerodynamic control ability, saving the energy of the electric propulsion system and improving the orbit control and attitude control ability of the aircraft.

[0015] 2. Secondly, the solar cell panels are used to supply power to the entire aircraft to ensure the stable flight of the aircraft and the energy supply for orbit control and attitude control. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only some embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0017] Figure 1A first isometric view of an air-breathing electric propulsion upper atmosphere aircraft with wing-assisted control according to the present invention; Figure 2 A second isometric view of an air-breathing electric propulsion upper atmosphere aircraft with wing-assisted control according to the present invention; Figure 3 A schematic diagram of a deflection and folding assembly of an air-breathing electric propulsion upper-atmosphere aircraft with wing-assisted control according to the present invention; Figure 4 This is a schematic structural diagram of an air intake system for an air-breathing electric propulsion upper-atmosphere aircraft with wing-assisted control according to the present invention; Figure 5 for Figure 3 A diagram showing the state of the male hinge and female hinge of the hinge structure of the folding assembly when they are pressed together by magnetic force; Figure 6 for Figure 3 A diagram showing the state of the hinge structure of the folding assembly when the male hinge and the female hinge are separated and locked by an electromagnetic spring pin; Figure 7 Schematic diagram of the relationship between the lift-to-drag ratio and the angle of attack obtained by simulating the upper atmosphere aircraft in an embodiment of the present invention.

[0018] In the figure: 1. Folding wing; 2. Deflection and folding assembly; 3. Main body; 4. Solar panel; 5. Air inlet; 6. Electric drive system; 7. Hinge structure; 8. Connecting frame; 9. Main wing; 10. Deflection axis; 11. Intake and contraction section; 12. Straight conveying section; 13. Electric propulsion; 14. Female hinge; 15. Pin; 16. Torsion spring; 17. Male hinge; 18. Elastic latch; 19. Electromagnetic spring pin. DETAILED DESCRIPTION

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0020] The present invention is an embodiment of an air-breathing electric propulsion upper atmosphere aircraft with wing-assisted control. The upper atmosphere aircraft in this embodiment is an aircraft flying at 86 to 600 km, such as Figure 1As shown, the aircraft comprises: a main body 3, a deflection folding assembly 2, an electric drive system 6 and a power supply system, the main body 3 is provided with main wings 9 on opposite sides, and the head of the main body 3 is provided with an air intake system; the deflection folding assembly 2 is arranged on the main wing 9, and the output end of the deflection folding assembly 2 is connected with the folding wing 1; the deflection folding assembly 2 is arranged on the main wing 9, and the output end of the deflection folding assembly 2 is connected with the folding wing 1; the deflection folding assembly 2 is used for locking the position of the folding wing 1 folded on the main wing 9 before the aircraft takes off, and is used for actively unlocking the main wing 9 after the aircraft enters the orbit to make the folding wing 1 unfold and lock the position of the unfolded folding wing 1; when the folding wing 1 of the aircraft is in an unfolded state, the folding wing 1 is driven to deflect to adjust the deflection angle of the folding wing 1 relative to the surface of the main wing 9; the electric drive system 6 is arranged at the tail of the main body 3, and the working medium inlet of the electric drive system 6 is communicated with the outlet of the air intake system; the power supply system is used for supplying power to the electric drive system and the deflection folding assembly 2; wherein the air intake system is used for capturing the rare nitrogen and oxygen in the super-low orbit environment, and compressing the nitrogen and oxygen as the working medium source of the electric drive system 6; the electric drive system 6 is used for storing, ionizing and accelerating the inhaled working medium to be sprayed out and generate thrust to maintain the power of the aircraft in orbit flight.

[0021] For example, in a specific embodiment, the deflection folding assembly 2 comprises: a deflection assembly and a folding assembly, the deflection assembly comprises: a rudder, the rudder is fixed to the bottom of the main wing 9, the output end of the rudder is connected with a deflection shaft 10, the end of the deflection shaft 10 is provided with a connecting frame 8, the connecting frame 8 is connected with the folding wing 1 through a hinge structure 7; the rudder drives the connecting frame 8 to drive the folding wing 1 to deflect through the deflection shaft 10, so as to adjust the deflection angle of the folding wing 1 relative to the surface of the main wing 9; the folding assembly comprises: a torsion spring 16 arranged on the hinge structure 7 and a locking assembly, the locking assembly is used for locking the folding wing 1 when the folding wing 1 is folded on the main wing 9 through the hinge structure 7, or is used for actively unlocking the folding wing 1 to make the folding wing 1 unfold under the torsion of the torsion spring 16.

[0022] In a specific embodiment, the hinge structure 7 comprises: a female hinge 14 and a male hinge 17, the male hinge 17 is rotatably connected with the female hinge 14 through a pin shaft 15; wherein the free end of the female hinge 14 is connected with the connecting frame 8, the free end of the male hinge 17 is connected with the folding wing 1, the torsion spring 16 is sleeved on the pin shaft 15, and one free end of the torsion spring 16 is connected with the female hinge 14 on the main wing 9, and the other free end of the torsion spring 16 is connected with the male hinge 17 of the folding wing 1.

[0023] In one specific embodiment, the locking assembly comprises: an electromagnetic ejector 19 arranged on the male hinge 17; and the end surface of the female hinge 14 is provided with a pin hole; the elastic pin 18 at the output end of the electromagnetic ejector 19 corresponds to the pin hole when the folding wing 1 is unfolded; the female hinge 14 and the male hinge 17 are both made of electromagnetic material, and when the folding wing 1 is folded on the main wing 9 around the hinge structure 7, the male hinge 17 and the female hinge 14 are powered on by the power supply, and the male hinge 17 and the female hinge 14 are magnetically connected to realize the folding position locking of the folding wing 1; after the aircraft enters the orbit, the power supply of the male hinge 17 and the female hinge 14 is turned off, the folding wing 1 rotates around the hinge structure 7 under the torsion of the torsion spring 16 to unfold, and the elastic pin 18 of the electromagnetic ejector 19 driven by the electromagnetic ejector 19 is inserted into the pin hole to lock the unfolded folding wing 1 in the unfolded position.

[0024] In one specific embodiment, the air intake system comprises an air intake channel 5 arranged inside the main body 3 along the length direction of the main body 3, the inlet of the air intake channel 5 faces the head of the main body 3, the outlet of the air intake channel 5 faces the tail of the main body 3, and the outlet of the air intake channel 5 is communicated with the working medium inlet of the electric drive system 6.

[0025] In one specific embodiment, the air intake channel 5 comprises: an air suction contraction section 11, the outlet of which is connected with a straight conveying section 12, and the outlet of the straight conveying section 12 is communicated with the inlet of the electric drive system 6, wherein the air suction contraction section 11 is used to collect the rarefied nitrogen and oxygen gas in the super-low orbit environment, compress the nitrogen and oxygen gas, and accelerate the delivery to the straight conveying section 12, the straight conveying section 12 is used to deliver the compressed working medium to the electric drive system 6, and the electric drive system 6 is used to ionize the working medium entering the straight conveying section 12 and input to accelerate the ejection to generate thrust.

[0026] In one specific embodiment, the electric drive system 6 adopts an electric thruster 13, the working medium inlet of the electric thruster 13 is communicated with the outlet of the straight conveying section 12, and the electric thruster 13 is used to ionize the working medium entering the straight conveying section 12 and input to accelerate the ejection to generate thrust.

[0027] In one specific embodiment, the power supply system comprises a plurality of solar panels 4 arranged in an array on the surface of the folding wing 1, the main wing, and the main body 3, which converts solar energy into electrical energy and stores it in the battery; it should be noted that the battery is used to supply power to the electric drive system 6 of the aircraft, the rudder of the deflection and folding assembly 2, the female hinge 14, the male hinge 17, and the electromagnetic ejector 19.

[0028] It should be noted that the main role of the main body 3 is to bear the function of the aircraft platform, used for connecting various devices and components, and used for placing various instruments, which is the base body of the whole aircraft; the main function of the solar panel 4 is to convert solar energy into electrical energy, used for power supply of the electric propulsion system 6 and the rudder of the deflection folding assembly 2, the female hinge 14, the male hinge 17 and the electromagnetic spring pin 19; the main function of the air inlet channel 5 is to collect the rare nitrogen and oxygen gas in the super low orbit environment, that is, the nitrogen and oxygen gas is captured and compressed by the suction contraction section 11 of the air inlet channel 5, and the compressed gas is transported to the electric thruster 13 of the electric drive system 6 through the straight line conveying section 12 to serve as the working medium source of the electric thruster 13; the main function of the electric thruster 13 is to suck and store the working medium, compress the working medium, transport the working medium to the electric thruster 13 for ionization and acceleration, and generate thrust in the process, which serves as the power for maintaining the low orbit aircraft orbit.

[0029] Working principle When the aircraft is put into the load cabin, the folding wing 1 is folded on the main wing 9 around the hinge structure 7 by manual compression, the power supply of the female hinge 14 and the male hinge 17 of the hinge structure 7 is turned on, so that the electromagnetic attraction force between the female hinge 14 and the male hinge 17 is generated, the female hinge 14 and the male hinge 17 of the hinge structure 7 are locked and compressed, when the hinge structure 7 is in the compressed state, the elastic plate 21 of the electromagnetic spring pin 19 is closed, and the elastic latch 18 of the electromagnetic spring pin 19 is not extended; after the aircraft enters the orbit, the female hinge 14 and the male hinge 17 of the hinge structure 7 are controlled to be powered off, at this time the folding wing 1 is unfolded under the torsion of the torsion spring 16, when the hinge structure 7 is unfolded in place, the elastic plate 21 of the electromagnetic spring pin 19 is controlled to be opened, the elastic latch 18 is inserted into the pin hole 20 in the side wall of the female hinge 14, and the unfolded folding wing 1 is locked to prevent the folding wing 1 from rebounding. Subsequently, the rudder of the folding assembly of the deflection folding assembly 2 can be controlled to work, the rudder drives the deflection shaft 10 to rotate, so that the deflection shaft 10 drives the folding wing 1 to produce a certain deflection angle relative to the surface of the main wing 9 through the connecting frame 8, so as to realize the adjustment of the aerodynamic lift-drag ratio of the aircraft; wherein the control and driving process of the folding wing 1 of the aircraft are powered by the solar panel 4.

[0030] The following will be described in combination with simulation data: The data in Table 1 is used as the flight environment data of the aircraft, the air inlet channel 5 of the aircraft adopts a concave type, and DSMC is used for simulation, and the attack angle of the aircraft body is kept at 0 degrees.

[0031] Table 1

[0032] The aircraft and model parameters used for simulation are shown in Table 2.

[0033] Table 2

[0034] The simulation result of DSMC is that the net thrust of the electric propulsion system 6 in the orbit of 180 km is 5.7 mN. If the wing surface GSI of the spacecraft adopts the CLL model, wherein, is the tangential energy adaptation coefficient, the net drag of the outer surface of the spacecraft is 3.84 mN. At this time, the thrust of the spacecraft minus the drag of the outer surface of the spacecraft still has a thrust surplus of about 1.86 mN. If the tip wing surface is deflected, the thrust surplus can be used to generate a certain lift. For example, the wing surface GSI is the CLL model, , the lift-drag ratio at the attack angle of 10 degrees is 1.2288 (the relationship between the lift-drag ratio coefficient of the spacecraft and the attack angle is shown in Figure 6 ). At this time, the spacecraft has a thrust surplus of 1.86 mN, which can generate a net lift of 2.29 mN, and the wing surface area of the deflected wing 1 is 0.673 m 2 .

[0035] The above only describes the preferred embodiments of the present application and is not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A wing-surface-aided controlled air-breathing electric propulsion upper-atmosphere vehicle, characterized by, The application relates to a spacecraft, which comprises the following parts: a main body, which is provided with main wings on opposite sides and is provided with an air inlet system at the head; a deflection and folding assembly arranged on the main wing, which is connected with a folding wing at the output end, and is used for locking the position of the folding wing folded on the main wing before the aircraft takes off, is used for actively unlocking the main wing to make the folding wing unfold and locking the position of the unfolded folding wing after the aircraft enters an orbit, and is used for driving the folding wing to deflect to adjust the deflection angle of the folding wing relative to the surface of the main wing when the folding wing is in an unfolded state; an electric driving system arranged at the tail of the main body, which is communicated with the outlet of the air inlet system through a working medium inlet; and a power supply system for supplying power to the electric driving system and the deflection and folding assembly; wherein the air inlet system is used for capturing rare nitrogen and oxygen in a super-low orbit environment, and compressing the nitrogen and oxygen to serve as the working medium source of the electric driving system; the electric driving system is used for storing, ionizing and accelerating the inhaled working medium to be sprayed out to generate thrust and maintain the power of the orbit flight of the aircraft.

2. An air-breathing electric propulsion upper atmospheric vehicle with wing-surface assisted control according to claim 1, characterized in that, The deflection and folding assembly comprises: a deflection assembly, which comprises a rudder fixed to the bottom of the main wing, and is connected with a deflection shaft at the output end; the end of the deflection shaft is provided with a connecting frame, and the connecting frame is connected with the folding wing through a hinge structure; the rudder drives the connecting frame to drive the folding wing to deflect through the deflection shaft, so as to adjust the deflection angle of the folding wing relative to the surface of the main wing; and a folding assembly, which comprises a torsion spring arranged on the hinge structure and a locking assembly; the locking assembly is used for locking the folding wing when the folding wing is folded on the main wing through the hinge structure, and is used for actively unlocking the folding wing to make the folding wing unfold and lock the position of the folding wing under the torsion of the torsion spring after the aircraft enters an orbit.

3. An air-breathing electric propulsion upper atmospheric vehicle with wing-surface assisted control according to claim 1, characterized in that, The hinge structure comprises: a female hinge; a male hinge connected with the female hinge through a pin shaft; wherein the free end of the female hinge is connected with the connecting frame, the free end of the male hinge is connected with the folding wing, the torsion spring is sleeved on the pin shaft, one free end of the torsion spring is connected with the female hinge on the main wing, and the other free end of the torsion spring is connected with the male hinge on the folding wing.

4. An air-breathing electric propulsion upper atmospheric vehicle with wing-surface assisted control according to claim 3, characterized in that, The locking assembly comprises: an electromagnetic elastic pin arranged on the male hinge; and the end surface of the female hinge is provided with a pin hole; the elastic pin of the output end of the electromagnetic elastic pin corresponds to the pin hole when the folding wing unfolds; wherein the female hinge and the male hinge are made of electromagnetic materials; when the folding wing is folded on the main wing through the hinge structure, the male hinge and the female hinge are electrified through a power supply, magnetic connection is generated between the male hinge and the female hinge to realize the position locking of the folding wing; after the aircraft enters an orbit, the power supply of the male hinge and the female hinge is controlled to be disconnected, the folding wing rotates to unfold around the hinge structure under the torsion of the torsion spring, and the elastic pin of the electromagnetic elastic pin is driven to be inserted into the pin hole through the electromagnetic elastic pin to lock the unfolded position of the folding wing.

5. An air-breathing electric propulsion upper atmosphere vehicle with wing-surface assisted control according to claim 1, characterized in that, The air inlet system comprises an air inlet channel arranged inside the main body along the length direction of the main body; the inlet of the air inlet channel faces the head of the main body; the outlet of the air inlet channel faces the tail of the main body; and the outlet of the air inlet channel is communicated with the working medium inlet of the electric driving system.

6. An air-breathing electric propulsion upper atmosphere vehicle with wing-surface assisted control according to claim 5, characterized in that, The air inlet channel comprises: The suction contraction section is connected with a linear conveying section, and the outlet of the linear conveying section is communicated with the inlet of the electric driving system, wherein the suction contraction section is used for collecting the rarefied nitrogen and oxygen gas in the ultra-low orbit environment, compressing the nitrogen and oxygen gas, and accelerating the conveying of the nitrogen and oxygen gas to the linear conveying section; the linear conveying section is used for conveying the compressed working medium to the electric driving system; the electric driving system is used for ionizing the working medium entering the linear conveying section and inputting the working medium to accelerate the ejection to generate thrust.

7. An air-breathing electric propulsion upper atmosphere vehicle with wing-surface assisted control according to claim 6, characterised in that, The electric driving system adopts an electric thruster, the working medium inlet of the electric thruster is communicated with the outlet of the linear conveying section, and the electric thruster is used for ionizing the working medium entering the linear conveying section and inputting the working medium to accelerate the ejection to generate thrust.

8. An air-breathing electric propulsion upper atmosphere vehicle with wing-surface assisted control according to claim 1, characterized in that, The power supply system comprises a plurality of solar cell panels, and the plurality of solar cell panels are arranged in an array on the surfaces of the folding wing, the main wing and the main body; the solar cell panels are used for converting solar energy into electric energy and storing the electric energy in a battery; and the battery is used for supplying electric energy to the electric driving system of the aircraft, the rudder of the deflection and folding assembly, the female hinge, the male hinge and the electromagnetic spring pin.

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