A plane-symmetrical high-speed aircraft

Abstract

The present invention discloses a plane-symmetrical high-speed aircraft, belonging to the field of aerospace technology, comprising an aircraft body, a vertical tail and a V-shaped tail, wherein the aircraft body has two symmetry planes, the aircraft body comprises a first section, a second section, a third section and an aircraft tail, and the vertical tail and the V-shaped tail are respectively arranged on the outer surface of the third section. The beneficial effects of the present invention are as follows: by setting a horizontal symmetry plane and a vertical symmetry plane, on the one hand, the aircraft can reduce the aerodynamic heat on the surface by flipping during flight, thereby reducing the surface temperature, which is conducive to selecting more conventional materials, reducing manufacturing costs, and improving the use conditions and life of the aircraft; on the other hand, the aircraft shape can be constructed with a small number of parameters and a simple cross-sectional shape, which reduces the difficulty of aerodynamic design and structural design and facilitates processing and manufacturing.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a plane-symmetrical high-speed aircraft. Background Art

[0002] During the flight of a high-speed aircraft, long-term air friction forms extremely high aerodynamic heating. The upper surface of the wing is directly exposed to the airflow and is more affected by the aerodynamic heating effect, while the lower surface of the wing is affected by airflow separation and turbulence and is less affected by the aerodynamic heating effect. Therefore, the temperature of the upper surface of the aircraft is usually significantly higher than that of the lower surface. A unified material system needs to give priority to the high temperature of the upper surface and select more high-temperature resistant materials, which will increase costs, or select conventional materials, which will reduce flight conditions. In addition, common aircraft generally have complex shapes, while plane-symmetrical aircraft can reduce the difficulty of designing the aircraft's system and shape, and can also reduce the difficulty of controlling aspects such as torque balance. Summary of the invention

[0003] The purpose of the present invention is to propose a plane-symmetrical high-speed aircraft in order to solve the above-mentioned technical problems.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions:

[0005] A plane-symmetrical high-speed aircraft comprises an aircraft body, a vertical tail and a V-shaped tail, wherein the aircraft body has two symmetry planes, the aircraft body comprises a first section, a second section, a third section and an aircraft tail, the outer structures of the first section, the second section and the third section have a continuous and smooth transition, the aircraft tail is a hexagon, and the vertical tail and the V-shaped tail are respectively arranged on the outer surface of the third section.

[0006] As a further description of the above technical solution:

[0007] The two symmetry planes are respectively a horizontal symmetry plane and a vertical symmetry plane. The first section is overall conical and has an aircraft head at the smaller end. The second section is overall circular and gradually turns into a rhombus. The first section and the second section first-second section interface are circular. The second section and the third section second-third section interface are rhombus and are face-symmetrical along the horizontal symmetry plane and the vertical symmetry plane. Two third section platforms are provided on the surface of the third section close to the tail of the aircraft. The two third section platforms are triangular in shape. The cross-sectional shape of the tail of the aircraft is hexagonal and is face-symmetrical along the horizontal symmetry plane and the vertical symmetry plane.

[0008] As a further description of the above technical solution:

[0009] There are two vertical tail wings, which are respectively rotatably arranged on two third-section platform surfaces close to the tail of the aircraft. The cross-sectional shapes of the two vertical tail wings are trapezoidal, and the two vertical tail wings are respectively perpendicular to the third-section platform surfaces.

[0010] As a further description of the above technical solution:

[0011] There are four V-shaped tail wings, which are respectively rotatably arranged on the side of the third section close to the tail of the aircraft, and the cross-sectional shape of the V-shaped tail wings is a trapezoid.

[0012] As a further description of the above technical solution:

[0013] The edges of the aircraft body are all provided with rounded corners, and the center of gravity of the aircraft body is located at 40%-70% of the overall length.

[0014] As a further description of the above technical solution:

[0015] The third section is provided with two connecting plates for installation at the tail of the aircraft, and the third section is provided with a circulation component for air circulation;

[0016] The circulation component includes a mounting plate arranged inside the third section and two tubes penetrating the surface of the mounting plate, the upper and lower ends of the two tubes are respectively fixed with frustum covers, one of the tubes is provided with a first sealing ball matching with the frustum cover, and the other tube is provided with a second sealing ball matching with the frustum cover, the weight of the second sealing ball is greater than the weight of the first sealing ball, the upper and lower ends of the first sealing ball are respectively connected with the upper and lower ends of the second sealing ball by a pull rope, the surface of the mounting plate is provided with a guide roller matching with the pull rope through the rotation of the support plate, and the surface of the mounting plate is provided with a driving member for driving air circulation.

[0017] As a further description of the above technical solution:

[0018] The driving component includes a fan and a refrigerator fixed on the surface of the mounting plate, the refrigerator input end is connected to the interior of one of the tube bodies through a pipeline, the refrigerator output end is connected to the fan input end through a pipeline, and the fan output end is connected to the interior of the other tube body through a pipeline, a plurality of ventilation holes are opened through the surface of the mounting plate, a controller is fixed on the surface of the mounting plate, and the fan and refrigerator are electrically connected to the controller respectively.

[0019] As a further description of the above technical solution:

[0020] The surface of the mounting plate is provided with a mounting hole for installing the pipe body, and the pipe body includes a first connecting sleeve and a second connecting sleeve. The surface of the first connecting sleeve is provided with a through hole for pipeline connection, and the outer surfaces of the first connecting sleeve and the second connecting sleeve are provided with threaded rings and are threadedly connected to the mounting hole. A sealing ring is provided between the first connecting sleeve and the second connecting sleeve, and the end surfaces of the first connecting sleeve and the second connecting sleeve are provided with annular grooves that match the sealing rings.

[0021] As a further description of the above technical solution:

[0022] The second sealing ball is made of iron material, and the end surface of the frustum cover at the upper and lower ends of one of the tube bodies is provided with an electromagnet for generating magnetism of the frustum cover, and the two electromagnets are electrically connected to the controller respectively. The two pull ropes are respectively provided with sliding sleeves at one end close to the second sealing ball, and the two sliding sleeves are provided with blocking rings on the opposite sides. Pressure sensors are fixedly provided on the inner walls of the two sliding sleeves, and the two pressure sensors are electrically connected to the controller respectively. Blocks matching the pressure sensors are fixedly provided on the surfaces of the two pull ropes. The sliding sleeves are made of iron material, and a ring matching the pull rope is fixedly provided on the inner wall of the sliding sleeve through a connecting rod.

[0023] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0024] In the present invention, by setting the horizontal symmetry plane and the vertical symmetry plane, on the one hand, the aerodynamic heat on the surface of the aircraft can be reduced by flipping during flight, thereby reducing the surface temperature, which is conducive to selecting more conventional materials, reducing manufacturing costs, and improving the use conditions and life of the aircraft. On the other hand, the aircraft shape can be constructed with a small number of parameters and a simple cross-sectional shape, which reduces the difficulty of aerodynamic design and structural design and facilitates processing and manufacturing.

[0025] In the present invention, by arranging a tube body, a frustum cover, a first sealing ball, a second sealing ring, a pull rope, a refrigerator and a fan, the effect of blowing air to the inner top surface of the third section is achieved, and heat is exchanged between the lower surface and the upper surface of the aircraft, which effectively prevents the upper surface of the aircraft from heating up quickly. At the same time, when the aircraft is turning over, the second sealing ring is always at the bottom under the action of gravity, so that after the aircraft is turned over, the effect of blowing air to the inner top surface of the third section can still be maintained. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 The appearance of a high-speed aircraft provided according to an embodiment of the present invention is shown;

[0027] Figure 2 A schematic diagram of the tail structure of a high-speed aircraft provided according to an embodiment of the present invention is shown;

[0028] Figure 3 It shows a schematic diagram of the structure of the first and second sections of the interface provided according to an embodiment of the present invention;

[0029] Figure 4 It shows a schematic diagram of the second three-segment interface structure provided according to an embodiment of the present invention;

[0030] Figure 5 A schematic diagram of the structure of the third section and the tail of the aircraft in a state of being separated according to an embodiment of the present invention is shown;

[0031] Figure 6 A schematic diagram of the structure of a circulation component provided in an embodiment of the present invention is shown;

[0032] Figure 7 A partial structural cross-sectional view of a circulation component provided according to an embodiment of the present invention is shown;

[0033] Figure 8 It shows a schematic diagram of the partial structure explosion of a circulation component provided in an embodiment of the present invention;

[0034] Fig. 9 A schematic diagram showing the cooperation between the second sealing ball and the sliding sleeve provided in an embodiment of the present invention is shown;

[0035] Fig.10 A cross-sectional view of a sliding sleeve structure provided according to an embodiment of the present invention is shown.

[0036] Legend: 100, aircraft body; 1, first section; 2, second section; 3, third section; 31, third section platform; 4, aircraft tail; 51, vertical tail; 52, V-shaped tail; 11, aircraft head; 12, first and second section interface; 23, second and third section interface; 61, horizontal symmetry plane; 62, vertical symmetry plane; 7, connecting plate; 8, mounting plate; 901, fan; 902, refrigerator; 903, vent; 904, Controller; 905, cone cover; 906, pull rope; 907, guide roller; 908, sleeve block; 909, first sealing ball; 910, sliding sleeve; 911, first connecting sleeve; 912, electromagnet; 913, mounting hole; 914, sealing ring; 915, annular groove; 916, second connecting sleeve; 917, through hole; 918, blocking ring; 919, pressure sensor; 920, sleeve ring; 921, connecting rod; 922, second sealing ball. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0038] like Figure 1-Figure 4 As shown, a plane-symmetrical high-speed aircraft includes an aircraft body 100, a vertical tail 51 and a V-shaped tail 52. The aircraft body 100 has two symmetry planes. The aircraft body 100 includes a first section 1, a second section 2, a third section 3 and an aircraft tail 4. The outer structures of the first section 1, the second section 2 and the third section 3 are continuously and smoothly transitioned. The aircraft tail 4 is a hexagon. The vertical tail 51 and the V-shaped tail 52 are respectively arranged on the outer surface of the third section 3.

[0039] Furthermore, the two symmetry planes are respectively a horizontal symmetry plane 61 and a vertical symmetry plane 62. The first section 1 is in a cone shape as a whole and a smaller end is provided with an aircraft head 11, and the degree of the cone angle is 3-20 degrees. The second section 2 is in a circular shape as a whole and gradually changes into a rhombus shape. The first section 1 and the second section 2 have a first-second section interface 12 that is circular, and its diameter is 100mm-200mm, and its diameter is larger than the spherical radius of the aircraft head 11. The second section 2 and the third section 3 have a second-third section interface 23 that is rhombus-shaped and is plane-symmetrical along the horizontal symmetry plane 61 and the vertical symmetry plane 62. The lengths of the two diagonal sides of the rhombus are both greater than the diameter of the circular cross-section of the interface 12 of the first and second sections, the side length of the rhombus is 200mm-500mm, and two third-section platforms 31 are provided on the surface of the third section 3 close to the side of the aircraft tail 4. The two third-section platforms 31 are triangular in shape, and the cross-sectional shape of the aircraft tail 4 is hexagonal and is face-symmetrical along the horizontal symmetry plane 61 and the vertical symmetry plane 62. The distance between the two horizontal sides of the hexagon is 300mm-800mm, and the longest diagonal of the hexagon is 600mm-1500mm.

[0040] Furthermore, there are two vertical tail wings 51, which are respectively rotatably arranged on the surfaces of the two third-section platforms 31 close to the side of the tail 4 of the aircraft. The cross-sectional shape of the two vertical tail wings 51 is trapezoidal and the sweep angle is 20-60 degrees. The two vertical tail wings 51 are respectively perpendicular to the surfaces of the third-section platforms 31. The vertical tail wings 51 can rotate along an axis perpendicular to the third-section platforms 31, so as to control the direction of the aircraft.

[0041] Furthermore, there are four V-shaped tail fins 52 which are respectively rotatably arranged on the side of the third section 3 close to the tail 4 of the aircraft. The cross-sectional shape of the V-shaped tail fins 52 is trapezoidal and the sweep angle is 20-60 degrees. Each V-shaped tail fin 52 can be rotated individually along an axis perpendicular to the side of the third section 3, thereby controlling the direction of the aircraft.

[0042] Furthermore, the edges of the aircraft body 100 are all chamfered to avoid aerodynamic losses caused by sharp edges. The overall length of the aircraft is 3000mm-6000mm, the center of gravity of the aircraft body 100 is located at 40%-70% of the overall length, and the outer structure of the aircraft body 100 is made of composite materials or metal materials.

[0043] Furthermore, the aircraft body 100 can manipulate the vertical tail 51 and the V-shaped tail 52 through the control system to achieve the upside-down flipping of the aircraft body 100 during high-speed flight. Through the upside-down flipping of the fuselage, the aircraft shape on one side can be prevented from being subjected to excessive aerodynamic heat, thereby extending the flight life and improving the flight limit. The aircraft can be equipped with an engine or a booster rocket to achieve high-speed flight. The engine includes one or a combination of an aviation engine, a space engine, a ramjet engine, an aerospace combined power, etc. The booster rocket includes a liquid rocket, a solid rocket, etc.

[0044] like Figure 1-Figure 10 As shown, a plane-symmetrical high-speed aircraft comprises an aircraft body 100, a vertical tail 51 and a V-shaped tail 52. The aircraft body 100 has two symmetric planes. The aircraft body 100 comprises a first section 1, a second section 2, a third section 3 and an aircraft tail 4. The outer structures of the first section 1, the second section 2 and the third section 3 are continuously and smoothly transitioned. The aircraft tail 4 is a hexagon. The vertical tail 51 and the V-shaped tail 52 are respectively arranged on the outer surface of the third section 3. Two connecting plates 7 for mounting the aircraft tail 4 are arranged inside the third section 3. A circulation component for air circulation is arranged inside the third section 3.

[0045] The circulation component includes a mounting plate 8 arranged inside the third section 3 and two tubes penetrating the surface of the mounting plate 8, and a frustum cover 905 is fixedly provided at the upper and lower ends of the two tubes, respectively. A first sealing ball 909 matching with the frustum cover 905 is provided inside one of the tubes, and a second sealing ball 922 matching with the frustum cover 905 is provided inside the other tube. The weight of the second sealing ball 922 is greater than the weight of the first sealing ball 909. The upper and lower ends of the first sealing ball 909 are connected to the upper and lower ends of the second sealing ball 922 by a pull rope 906, respectively. A guide roller 907 matching with the pull rope 906 is provided on the surface of the mounting plate 8 for rotation through a support plate. A driving member for driving air circulation is provided on the surface of the mounting plate 8. Since the weight of the second sealing ball 922 is greater than the weight of the first sealing ball 909, the second sealing ball 922 will be at the bottom and contact with the inner wall of the frustum cover 905, and pull the first sealing ball 909 to be at the top and contact with the inner wall of the frustum cover 905 (refer to the attached figure of the instruction manual). Figure 7 ), and then under the action of the driving member, the circulation of the air inside the third section 3 will be promoted, that is, the air at the lower part of the third section 3 will be sucked by the driving member (entering from the lower end of the tube body on the left and then discharged from the upper end of the tube body on the right), and the top surface of the third section 3 will be blown, thereby improving the effect of cooling the upper surface of the aircraft. When the aircraft is turned over, the mounting plate 8 is driven to turn over. At this time, under the action of the gravity of the second sealing ball 922, the second sealing ball 922 is still at the bottom, that is, the air at the lower part of the third section 3 is always sucked and discharged to the upper part of the third section 3.

[0046] Furthermore, the driving component includes a fan 901 and a refrigerator 902 fixed on the surface of the mounting plate 8, the input end of the refrigerator 902 is connected to the inside of one of the tube bodies through a pipeline, the output end of the refrigerator 902 is connected to the input end of the fan 901 through a pipeline, and the output end of the fan 901 is connected to the inside of another tube body through a pipeline, a plurality of ventilation holes 903 are opened through the surface of the mounting plate 8, a controller 904 is fixedly provided on the surface of the mounting plate 8, the fan 901 and the refrigerator 902 are electrically connected to the controller 904 respectively, and the fan 901 and the refrigerator 902 are started, so that the air below the inside of the third section 3 is cooled by the refrigerator 902 and then discharged to the upper part of the inside of the third section 3, thereby improving the cooling effect.

[0047] Furthermore, a mounting hole 913 for installing the tube body is provided on the surface of the mounting plate 8, and the tube body includes a first connecting sleeve 911 and a second connecting sleeve 916. A through hole 917 for pipeline connection is provided on the surface of the first connecting sleeve 911. The outer surfaces of the first connecting sleeve 911 and the second connecting sleeve 916 are provided with threaded rings and are threadedly connected to the mounting hole 913. A sealing ring 914 is provided between the first connecting sleeve 911 and the second connecting sleeve 916. The end surfaces of the first connecting sleeve 911 and the second connecting sleeve 916 are provided with an annular groove 915 that matches the sealing ring 914. When in use, the staff respectively installs the first connecting sleeve 911 and the second connecting sleeve 916 in the mounting hole 913, so that the first connecting sleeve 911 and the second connecting sleeve 916 are connected to form the tube body. By setting the sealing ring 914, the sealing of the connection between the first connecting sleeve 911 and the second connecting sleeve 916 is effectively guaranteed.

[0048] Further, the second sealing ball 922 is made of iron material, and the end surface of the cone cover 905 at the upper and lower ends of one tube body is provided with an electromagnet 912 for generating magnetism of the cone cover 905, and the two electromagnets 912 are electrically connected to the controller 904 respectively. The two pull ropes 906 are respectively sleeved with sliding sleeves 910 at one end close to the second sealing ball 922, and the two sliding sleeves 910 are provided with blocking rings 918 on the opposite side. The inner walls of the two sliding sleeves 910 are respectively fixed with pressure sensors 919, and the two pressure sensors 919 are respectively electrically connected to the controller 904. The surfaces of the two pull ropes 906 are fixed with sleeve blocks 908 matching with the pressure sensors 919. The sliding sleeve 910 is made of iron material, and the inner wall of the sliding sleeve 910 is fixed with a ring 920 that slides with the pull rope 906 through a connecting rod 921. In the initial state (refer to the attached manual Figure 7 ), the second sealing ball 922 and the frustum cover 905 are in an adsorption state, which effectively ensures the stability of the second sealing ball 922, and then ensures the stability of the first sealing ball 909. When the aircraft is turned over, the second sealing ball 922 and the frustum cover 905 are in an adsorption state at first and will not move, but will cause the sliding sleeve 910 to slide. During the sliding process, the sliding sleeve 910 will contact the sleeve block 908, and then the pressure sensor 919 will contact the sleeve block 908, and the sliding sleeve 910 will be attracted by the magnetic force of the frustum cover 905, so that the pressure sensor 919 9 is subjected to the extrusion force and feeds back the signal to the controller 904. The controller 904 controls the electromagnet 912 on the cone cover 905 in contact with the second sealing ball 922 to cut off the power, and then releases the adsorption of the second sealing ball 922. At this time, the second sealing ball 922 slides, and the other electromagnet 912 is not cut off. At this time, the second sealing ball 922 will be adsorbed on the cone cover 905. The movement of the second sealing ball 922 drives the first sealing ball 909 to move through the pull rope 906, so that the first sealing ball 909 and the second sealing ball 922 are adjusted in position.

[0049] Furthermore, the two symmetry planes are respectively a horizontal symmetry plane 61 and a vertical symmetry plane 62, the first section 1 is overall conical and has an aircraft head 11 at the smaller end, the second section 2 is overall circular and gradually changes into a rhombus, the first two-section interface 12 between the first section 1 and the second section 2 is circular, the second three-section interface 23 between the second section 2 and the third section 3 is rhombus and is face-symmetrical along the horizontal symmetry plane 61 and the vertical symmetry plane 62, two third-section platforms 31 are provided on the surface of the third section 3 close to the aircraft tail 4, the two third-section platforms 31 are triangular in shape, and the cross-sectional shape of the aircraft tail 4 is hexagonal and is face-symmetrical along the horizontal symmetry plane 61 and the vertical symmetry plane 62.

[0050] Furthermore, there are two vertical tail wings 51 which are rotatably disposed on the surfaces of the two third-section platforms 31 close to the tail 4 of the aircraft. The cross-sectional shape of the two vertical tail wings 51 is trapezoidal, and the two vertical tail wings 51 are perpendicular to the surfaces of the third-section platforms 31 .

[0051] Furthermore, there are four V-shaped tail wings 52 which are rotatably disposed on the side of the third section 3 close to the tail 4 of the aircraft, and the cross-sectional shape of the V-shaped tail wings 52 is a trapezoid.

[0052] Furthermore, the edges of the aircraft body 100 are all provided with rounded corners, and the center of gravity of the aircraft body 100 is located at 40%-70% of the overall length.

[0053] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A plane-symmetrical high-speed aircraft, comprising an aircraft body (100), a vertical tail (51) and a V-shaped tail (52), characterized in that: The aircraft body (100) has two symmetry planes, the aircraft body (100) comprises a first section (1), a second section (2), a third section (3) and an aircraft tail (4), the outer structures of the first section (1), the second section (2) and the third section (3) are continuously and smoothly transitioned, the aircraft tail (4) is hexagonal, and the vertical tail (51) and the V-shaped tail (52) are respectively arranged on the outer surface of the third section (3); The two symmetry planes are respectively a horizontal symmetry plane (61) and a vertical symmetry plane (62); the first section (1) is in a conical shape as a whole and is provided with an aircraft head (11) at its smaller end; the second section (2) is in a circular shape as a whole and gradually changes into a rhombus shape; the first section-two interface (12) between the first section (1) and the second section (2) is in a circular shape; the second section-three interface (23) between the second section (2) and the third section (3) is in a rhombus shape and is in a plane-symmetrical shape along the horizontal symmetry plane (61) and the vertical symmetry plane (62); two third section platforms (31) are provided on the surface of the third section (3) on one side close to the aircraft tail (4); the two third section platforms (31) are in a triangular shape; the cross-sectional shape of the aircraft tail (4) is in a hexagonal shape and is in a plane-symmetrical shape along the horizontal symmetry plane (61) and the vertical symmetry plane (62).

2. A plane-symmetrical high-speed aircraft according to claim 1, characterized in that: The number of the vertical tail wings (51) is two and they are rotatably arranged on the surfaces of the two third-stage platforms (31) close to the tail (4) of the aircraft. The cross-sectional shape of the two vertical tail wings (51) is a trapezoid. The two vertical tail wings (51) are perpendicular to the surfaces of the third-stage platforms (31).

3. A plane-symmetrical high-speed aircraft according to claim 2, characterized in that: There are four V-shaped tail wings (52) which are rotatably arranged on the side of the third section (3) close to the tail (4) of the aircraft, and the cross-sectional shape of the V-shaped tail wings (52) is a trapezoid.

4. A plane-symmetrical high-speed aircraft according to claim 1, characterized in that: The edges of the aircraft body (100) are all provided with rounded corners, and the center of gravity of the aircraft body (100) is located at a position of 40%-70% of the overall length.

5. The plane-symmetrical high-speed aircraft according to claim 1, characterized in that: The third section (3) is provided with two connecting plates (7) for mounting the tail (4) of the aircraft, and the third section (3) is provided with a circulation component for air circulation; The circulation component comprises a mounting plate (8) arranged inside the third section (3) and two tubes penetrating the surface of the mounting plate (8), wherein the upper and lower ends of the two tubes are respectively fixed with a frustum cover (905), wherein one of the tubes is provided with a first sealing ball (909) matching with the frustum cover (905), and the other tube is provided with a second sealing ball (922) matching with the frustum cover (905), the weight of the second sealing ball (922) is greater than the weight of the first sealing ball (909), the upper and lower ends of the first sealing ball (909) are respectively connected to the upper and lower ends of the second sealing ball (922) by a pull rope (906), the surface of the mounting plate (8) is provided with a guide roller (907) matching with the pull rope (906) through the support plate rotation, and the surface of the mounting plate (8) is provided with a driving member for driving air circulation.

6. A plane-symmetrical high-speed aircraft according to claim 5, characterized in that: The driving component comprises a fan (901) and a refrigerator (902) fixedly mounted on the surface of a mounting plate (8); an input end of the refrigerator (902) is connected to the interior of one of the tube bodies via a pipeline; an output end of the refrigerator (902) is connected to the input end of the fan (901) via a pipeline; and an output end of the fan (901) is connected to the interior of another tube body via a pipeline; a plurality of ventilation holes (903) are formed through the surface of the mounting plate (8); a controller (904) is fixedly mounted on the surface of the mounting plate (8); and the fan (901) and the refrigerator (902) are electrically connected to the controller (904) respectively.

7. A plane-symmetrical high-speed aircraft according to claim 6, characterized in that: The surface of the mounting plate (8) is provided with a mounting hole (913) for mounting the pipe body. The pipe body comprises a first connecting sleeve (911) and a second connecting sleeve (916). The surface of the first connecting sleeve (911) is provided with a through hole (917) for pipe connection. The outer surfaces of the first connecting sleeve (911) and the second connecting sleeve (916) are provided with threaded rings and are threadedly connected to the mounting hole (913). A sealing ring (914) is provided between the first connecting sleeve (911) and the second connecting sleeve (916). The end surfaces of the first connecting sleeve (911) and the second connecting sleeve (916) are provided with an annular groove (915) that matches the sealing ring (914).

8. A plane-symmetrical high-speed aircraft according to claim 7, characterized in that: The second sealing ball (922) is made of iron material, and the end surface of the cone cover (905) at the upper and lower ends of one of the tube bodies is provided with an electromagnet (912) for generating magnetism of the cone cover (905), and the two electromagnets (912) are respectively electrically connected to the controller (904). The two pull ropes (906) are respectively sleeved with sliding sleeves (910) at one end close to the second sealing ball (922), and the two sliding sleeves (910) are provided with blocking rings (918) on the opposite sides. The inner walls of the two sliding sleeves (910) are respectively fixed with pressure sensors (919), and the two pressure sensors (919) are respectively electrically connected to the controller (904). The surfaces of the two pull ropes (906) are fixed with sleeve blocks (908) matching with the pressure sensors (919). The sliding sleeve (910) is made of iron material, and the inner wall of the sliding sleeve (910) is fixed with a ring (920) that slidably matches with the pull rope (906) through a connecting rod (921).

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