Shunting jet-propelled aircraft

Abstract

The invention relates to the field of aircrafts, in particular to a split-flow jet aircraft. The device comprises an air injection mechanism, a shunting cabin, a flight control cabin, an air injection regulation and control mechanism and a telescopic empennage, the air injection mechanism injects air from top to bottom; the shunting cabin is arranged at the bottom of the air injection mechanism, the top of the shunting cabin is provided with an air inlet channel, and the periphery of the shunting cabin is provided with a plurality of uniformly-distributed shunting ports; the flight control cabin is arranged at the bottom of the shunting cabin; a plurality of groups of air injection regulation and control mechanisms are uniformly arranged on the periphery of the shunting cabin, introduce air injected from the shunting port, control the air circulation range and inject the air downwards; and multiple groups of telescopic empennages are uniformly arranged around the shunting cabin. The turbine engine used in the invention is high in thrust efficiency, good in effect, safer and long in service life.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft, in particular to a split-flow jet aircraft. BACKGROUND

[0002] At present, low-altitude aircraft mainly includes the following three types: 1, helicopter, relying on rotor to provide lift and propulsion, is a kind of vertical take-off and landing aircraft. 2, unmanned aerial vehicle, through remote control or autonomous flight to realize flight, application range is very wide. 3, electric vertical take-off and landing aircraft, which is electrically driven, vertically takes off and lands, and combines the flexibility of the multi-rotor of the helicopter with the efficiency advantage of the fixed wing. Unmanned aerial vehicle technology is gradually mature, and the endurance, load, stability and obstacle avoidance capability are greatly improved, which can complete more complex tasks, such as long-distance inspection, precise spraying, emergency rescue and heavy logistics, etc.

[0003] At present, low-altitude aircraft is mainly rotorcraft, as the main source of power components, when the blade is in operation, the high-speed rotating blade is exposed outside, which has safety hazards, and the service life of the blade part is short. SUMMARY

[0004] The present application aims at the problems in the background art, and provides a split-flow jet aircraft, which has high turbine engine thrust efficiency, good effect, is safer and has long service life.

[0005] The technical scheme of the present application provides a split-flow jet aircraft, which comprises a jet mechanism, a split-flow cabin, a flight control cabin, a jet control mechanism and a telescopic tail wing. The jet mechanism sprays air from top to bottom. The split-flow cabin is arranged at the bottom of the jet mechanism, the top of the split-flow cabin is provided with an air inlet channel, and the outer periphery of the split-flow cabin is provided with a plurality of evenly distributed split-flow openings. The flight control cabin is arranged at the bottom of the split-flow cabin. The jet control mechanism is evenly arranged in multiple groups around the split-flow cabin, introduces the air sprayed from the split-flow opening, controls the air flow range, and sprays the air downward. The telescopic tail wing is evenly arranged in multiple groups around the split-flow cabin.

[0006] Preferably, the jet mechanism comprises a support cylinder, a turbine engine and an oil tank. The cross section of one side of the support cylinder is in the shape of an inverted "U". A grating plate is arranged on the inner side of the hollow of the support cylinder. The turbine engine is arranged in the support cylinder. The oil tank is arranged at the bottom of the grating plate to supply oil for the turbine engine.

[0007] Preferably, the split-flow cabin is provided with a convex flow guide surface in the middle part. The flow guide surface guides the air sprayed downward by the jet mechanism to the circumferential split-flow openings.

[0008] Preferably, a plurality of air outlets are arranged in an inclined manner at the lower part of the split-flow cabin. The top end of the air outlet penetrates the flow guide surface. The outer periphery of the flight control cabin is provided with a heat dissipation opening.

[0009] Preferably, the jet control mechanism comprises a wing, a jet cylinder and a tuyere adjusting assembly, the wing and the jet cylinder are both in a cylindrical structure, the jet cylinder is arranged inside the wing, the wing is provided with a mounting port communicated with the flow dividing port, the jet cylinder is hollow inside, the jet cylinder is provided with an air inlet communicated with the mounting port on the side, the inner periphery of the top of the jet cylinder is provided with a circumferential jet port, the jet port is inclined downward, and the tuyere adjusting assembly is arranged at the air inlet of the jet cylinder to control the flow range of air at the air inlet.

[0010] Preferably, a grid frame is arranged inside the hollow jet cylinder.

[0011] Preferably, the tuyere adjusting assembly comprises an upper plate and a lower plate arranged on the jet cylinder, a rack I arranged on the upper plate, a motor arranged on the upper plate and a plurality of groups of wind blocking assemblies arranged side by side, the wind blocking assembly comprises a rotating shaft arranged on the upper plate and the lower plate, a vane plate arranged on the rotating shaft and a gear I arranged on the rotating shaft and engaged with the rack I, and the motor is drivingly connected with one rotating shaft.

[0012] Preferably, the surfaces on both sides of the vane plate are arc-shaped, and the surfaces are uniformly provided with pits and grooves.

[0013] Preferably, the wing is provided with a mounting groove I on the side, and the retractable tail wing comprises a tail wing and a retracting assembly for controlling the linear movement of the tail wing.

[0014] Preferably, the wing is provided with a mounting groove II on the side, and the mounting groove II is provided with a landing gear assembly.

[0015] Compared with the prior art, the present application has the following beneficial technical effects:

[0016] The turbine engine used in the present application has high thrust efficiency and good effect, the turbine blades of the turbine engine are not exposed, it is safer and has a long service life, the structures in the aircraft are compact, the air resistance is low, the aircraft can take off and land vertically, it does not depend on the runway and has high flexibility. The air pressure and resistance in front of the aircraft are reduced, the air pressure at the bottom of the aircraft is increased, the air pressure in front is reduced, and the aircraft is easy to fly efficiently. The six-way flow dividing can change the movement direction and attitude of the aircraft with the change of thrust, and the control mode is unique. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a structural schematic view of the flow dividing jet aircraft;

[0018] Figure 2 It is a structural top view of Figure 1

[0019] Figure 3 It is a distribution schematic view of the supporting cylinder, the oil tank and the flow dividing cabin;

[0020] Figure 4 It is a structural schematic view of the flow dividing cabin;​

[0021] Figure 5 This is a structural diagram of the flight control cabin;

[0022] Figure 6 A schematic diagram of the external structure of a split-jet aircraft;

[0023] Figure 7 A schematic diagram of the jet control mechanism, telescopic tail fin, and landing gear assembly;

[0024] Figure 8 This is a partial structural diagram of the jet control mechanism;

[0025] Figure 9 This is a schematic diagram of the blade structure;

[0026] Figure 10 This is a schematic diagram of the jet tube structure;

[0027] Figure 11 This is a cross-sectional view of the jet tube structure;

[0028] Figure 12 for Figure 11 Enlarged view of the structure at point A in the image.

[0029] Reference numerals: 1. Support cylinder; 101. Grille plate; 2. Turbine engine; 3. Fuel tank; 4. Draft compartment; 400. Mounting surface; 401. Guide surface; 402. Draft port; 403. Exhaust port; 41. Flight control compartment; 5. Wing; 501. Mounting port; 502. Mounting slot one; 503. Mounting slot two; 6. Jet tube; 601. Air inlet; 602. Jet nozzle; 61. Enclosure section ; 62. Outer ring; 63. Inner ring; 64. Grille frame; 71. Upper plate; 72. Lower plate; 8. Motor; 9. Shaft; 10. Blade; 1001. Slot; 11. Gear 1; 12. Rack 1; 13. Tail wing; 14. Connecting plate; 15. Hinge plate; 16. Tail wing electric cylinder; 17. Support; 18. Gear 2; 19. Rack 2; 20. Landing gear; 21. Landing gear electric cylinder. Detailed Implementation

[0030] like Figures 1-12 As shown in the figure, the split-jet aircraft proposed in this embodiment includes a jet mechanism, a split-jet compartment 4, a flight control compartment 41, a jet control mechanism, a retractable tail fin, and a landing gear assembly.

[0031] like Figures 1-3As shown, the jet mechanism sprays air from top to bottom. The jet mechanism includes a support cylinder 1, a turbine engine 2 and an oil tank 3. The support cylinder 1 has a cross-section profile of inverted "U" shape. A grid plate 101 is arranged on the hollow inner side of the support cylinder 1 to enhance structural strength. The oil tank 3 is arranged at the bottom of the grid plate 101 and at the top of a flow distribution cabin 4. The oil tank 3 can supply oil for the turbine engine 2. The turbine engine 2 is arranged inside the support cylinder 1 and is not exposed, which is safer for operation. The turbine engine 2 sprays air from top to bottom to generate high-pressure and high-speed air flow. By using the principle of air pressure, the high-speed turbine blades of the turbine engine 2 axially suck in air to generate high pressure and transport air. When sucking in air in front, the air in the space in front of the aircraft is sucked into the front part of the support cylinder 1 during flight, causing the front part of the aircraft to be a low-pressure area, and the aircraft generates forward thrust. Then, the high-pressure air is transported to the flow distribution cabin 4 to generate high-pressure and high-speed air flow.

[0032] As shown in Figure 3 and Figure 4 , the flow distribution cabin 4 is arranged at the bottom of the jet mechanism and is made of 580Mpa high-strength carbon plastic material. The flow distribution cabin 4 has an air inlet channel at the top and a plurality of uniformly distributed flow distribution ports 402, such as six uniformly distributed flow distribution ports 402, around the periphery. The cross-sectional area of the air inlet channel is equal to the sum of the cross-sectional areas of the six flow distribution ports 402. The flow distribution cabin 4 has a convex flow guide surface 401 in the middle, which is located between the plurality of flow distribution ports 402. The flow guide surface 401 guides the high-pressure and high-speed air flow sprayed downward by the jet mechanism to the circumferential plurality of flow distribution ports 402, so that the high-pressure and high-speed air flow sprayed downward by the turbine engine 2 can be distributed from multiple directions through the plurality of flow distribution ports 402.

[0033] As shown in Figures 3-5 , the flight control cabin 41 is arranged at the bottom of the flow distribution cabin 4 and is specifically installed at the recessed mounting surface 400 at the bottom of the flow distribution cabin 4. The lower part of the flow distribution cabin 4 is provided with a plurality of air outlets 403 distributed obliquely. The top end of the air outlet 403 penetrates the flow guide surface 401. The air sprayed downward by the turbine engine 2 can also be sprayed downward through the air outlet 403, which is conducive to forming spiral turbulent flow and dispersing the tail vortex when the aircraft moves forward, thereby improving flight efficiency. The flight control cabin 41 is provided with a battery pack, a distribution box, a flight control unit, an engine control unit and a refrigeration unit. The battery pack supplies power to electrical devices. The flight control unit can control the jet regulation mechanism, the retractable tail wing and the landing gear assembly to realize the control of the flight direction and the action of the retractable tail wing and the landing gear assembly. The engine control unit is used to control the operation of the turbine engine 2. The flight control cabin 41 is provided with a heat dissipation port around the periphery. The air sprayed from the air outlet 403 can also be used to ventilate and cool each structure inside the flight control cabin 41 through the heat dissipation port.

[0034] As shown in Figure 6As shown, multiple sets of jet control mechanisms are evenly arranged around the periphery of the splitter compartment 4, for example, six sets, forming a hexagonal ring structure for the aircraft. By controlling the jet speed through these six sets of jet control mechanisms, the aircraft's flight direction and speed can be adjusted. The jet control mechanisms are modularly designed and can be compactly combined. When one set of jet control mechanisms is damaged, it can be replaced individually, making disassembly and maintenance convenient. Each set of jet control mechanisms fits snugly against the two adjacent sets, forming a jet channel in the middle. The inner surface has an air intake channel communicating with the jet channel, introducing air from the splitter port 402, controlling the airflow range, and ejecting the air downwards.

[0035] like Figures 6-8 As shown, the jet control mechanism includes a wing 5, a jet tube 6, and vent adjustment components. Six sets of vent adjustment components control the opening and closing of corresponding air intake channels in six directions, achieving thrust splitting. High-pressure, high-speed air is supplied to the six jet nozzles 602 by the splitter compartment 4. The wing 5 is bolted to the splitter compartment 4 circumferentially. Both the wing 5 and the jet tube 6 are cylindrical structures with trapezoidal cross-sectional profiles. The jet tube 6 is hollow, forming an air passage in the center. A grid frame 64 is installed on the hollow inner side of the jet tube 6 to enhance its structural strength. The grid frame 64 has evenly distributed through holes to maintain airflow in the hollow inner area. The jet tube 6 is located inside the wing 5, which has an installation port 501 communicating with the splitter port 402. The installation port 501 serves as the air intake channel input. The jet tube 6 has an air inlet 601 on its side, which communicates with the mounting port 501. The top inner circumference of the jet tube 6 has a circumferential jet nozzle 602, which serves as the output end of the air intake channel. The jet nozzle 602 is angled downwards. High-pressure, high-speed air from the splitter 4, passing through the jet nozzle 602 (which has a large circumferential length and a small width), generates a high-speed jet, driving surrounding air backwards and amplifying the thrust effect. An airflow adjustment assembly is located at the air inlet 601 of the jet tube 6, regulating the airflow range at the air inlet 601, thereby controlling the speed of the air ejected through the jet nozzle 602. A smaller flow range results in a smaller volume of air, a lower airflow speed at the jet nozzle 602, and a smaller thrust. By adjusting the airflow adjustment assemblies in six directions, thrust can be adjusted in six directions, thus coordinating and controlling the aircraft's flight direction.

[0036] like Figures 10-12As shown, the air jet cylinder 6 comprises a surrounding cylinder part 61, an outer ring part 62 and an inner ring part 63. The surrounding cylinder part 61 is U-shaped in cross section, with the U-shaped opening facing upwards. The air inlet 601 is located on the outer side of the surrounding cylinder part 61. The outer ring part 62 is ring-shaped, with the cross section being inverted V-shaped. The outer periphery bottom end of the outer ring part 62 is integrally connected to the outer periphery top end of the surrounding cylinder part 61, and the inner side bottom end of the outer ring part 62 is located above the inner side of the surrounding cylinder part 61. The inner ring part 63 is ring-shaped, with the cross section being inverted V-shaped. The inner side bottom end of the inner ring part 63 is integrally connected to the inner side top end of the surrounding cylinder part 61, and the inner ring part 63 is located inside the outer ring part 62. The air jet opening 602 is located between the inner side bottom end of the outer ring part 62 and the inner side bottom end of the inner ring part 63. The air entering the air jet cylinder 6 from the air inlet 601 can spread in the circumferential direction through the through holes on the grid frame 64, and then be sprayed out through the air jet opening 602 on the top, i.e. sprayed out obliquely downwards in the circumferential direction, to generate thrust. The air in front of the air jet cylinder 6 flows through the air channel in the middle, and cooperates with the high-pressure high-speed airflow sprayed out from the air jet opening 602 to provide thrust for the aircraft flight. The top end of the outer ring part 62 and the top end of the inner ring part 63 are smoothly transitioned, so that the air flow resistance is smaller and the flow is smoother.

[0037] As shown in Figure 8 , the air inlet adjusting assembly comprises an upper plate 71 and a lower plate 72 arranged on the air jet cylinder 6, a rack 12 slidingly arranged on the upper plate 71, a motor 8 arranged on the upper plate 71, and a plurality of groups of wind blocking assemblies arranged side by side. The degree of shielding of the air inlet 601 is adjusted by the wind blocking assemblies, and the degree of shielding is inversely proportional to the air flow range, i.e. the greater the degree of shielding, the smaller the air flow range, and ultimately the smaller the flow rate of the airflow sprayed out through the air jet opening 602, the smaller the thrust generated. The upper plate 71 and the lower plate 72 are located at the mounting port 501. The wind blocking assembly comprises a rotating shaft 9 rotatably arranged on the upper plate 71 and the lower plate 72, a leaf plate 10 arranged on the rotating shaft 9, and a gear 11 arranged on the rotating shaft 9 and meshingly connected with the rack 12. The motor 8 is drivingly connected with one rotating shaft 9. After the motor 8 drives the rotating shaft 9 to rotate, the rotating shaft 9 drives the rack 12 to slide through the gear 11. The rack 12 drives the remaining gears 11 to rotate, and the remaining gears 11 drive the respective rotating shafts 9 to rotate, so as to drive a plurality of leaf plates 10 to rotate by using a plurality of rotating rotating shafts 9. The degree of shielding of the air inlet 601 is adjusted by adjusting the distribution orientation of the plurality of leaf plates 10. When the plurality of leaf plates 10 are flush, the degree of shielding is the largest. The air flow range is adjusted by controlling the distribution of the plurality of leaf plates 10. The adjustment process is coordinated and unified, and the control effect is good.

[0038] As shown in Figure 9 , the surfaces on both sides of the leaf plate 10 are arc-shaped, and the surfaces are uniformly distributed with pits 1001 to achieve drag reduction and heat insulation.

[0039] As shown in Figure 6 and Figure 7As shown, the retractable tail wing is evenly provided with multiple groups, such as three groups, around the flow distribution cabin 4. The retractable tail wing comprises a tail wing 13 and a retractable assembly for controlling the linear movement of the tail wing 13. The outer side of the tail wing 13 is inclined, and the inclination gradually inclines outward from top to bottom. The retractable assembly comprises a connecting plate 14 provided at one end of the tail wing 13, a hinged plate 15 hinged at one end of the connecting plate 14, a tail wing electric cylinder 16 hinged at the moving end of the hinged plate 15, a support 17 for hinged installation of the tail wing electric cylinder 16, and a guide assembly for guiding the linear movement of the tail wing 13. The extension and retraction of the tail wing electric cylinder 16 can drive the hinged plate 15 to move, the hinged plate 15 drives the connecting plate 14 to move, the connecting plate 14 drives the tail wing 13 to move, and the guide assembly guides the tail wing 13 to move in a linear direction. The support 17 is arranged in the mounting groove one 502. For the hinge between the connecting plate 14, the hinged plate 15 and the tail wing electric cylinder 16, both ends and the middle part of the hinged plate 15 have hinge positions, the connecting plate 14 is hinged at the hinge position at one end of the hinged plate 15, and the moving end of the tail wing electric cylinder 16 is hinged at the hinge position at the other end or the middle part of the hinged plate 15. The outer circumferential surfaces of the opposite sides of the wing 5 are respectively provided with the mounting groove one 502 and the mounting groove two 503, and the extension and retraction of the tail wing electric cylinder 16 can extend the tail wing 13 out of the mounting groove one 502 or into the mounting groove one 502.

[0040] As shown in Figure 7 , the guide assembly comprises a mounting shaft rotatingly penetrating the tail wing 13, two gear wheels two 18 coaxially arranged on the mounting shaft, and two racks two 19 arranged in the mounting groove one 502, and the gear wheels two 18 correspond to and are connected with the racks two 19. The rack two 19 is parallel to the tail wing 13. When the tail wing 13 moves linearly, the mounting shaft will move, the mounting shaft drives the gear wheels two 18 to move, the gear wheels two 18 roll on the racks two 19, and the guide assembly can assist the linear movement of the tail wing 13. The extension and retraction of the tail wing electric cylinder 16 can realize the extension and retraction of the tail wing 13, and the control operation is simple. After the tail wing 13 is extended, the aircraft basically stops rotating during flight, at this time, at the inclined air outlet 403, the rotating force can only disperse the vortex to change the direction, and the force is too small to affect the direction of the entire aircraft.

[0041] As shown in Figure 6 and Figure 7As shown, three sets of landing gear assemblies are evenly arranged, with the three sets of landing gear assemblies and three sets of retractable tail fins staggered, forming a hexagonal overall structure. The landing gear assemblies are located in mounting slot 2 503 and include hinge seat 1, hinge seat 2, landing gear 20, and landing gear electric cylinder 21. One end of landing gear 20 is a wheel, and the other end is hinged to hinge seat 1. Landing gear 20 can extend downwards from mounting slot 2 503 and can also retract into mounting slot 2 503. Landing gear electric cylinder 21 is hinged at both ends to landing gear 20 and hinge seat 2, respectively. Both hinge seat 1 and hinge seat 2 are located within mounting slot 2 503 of wing 5. When landing gear electric cylinder 21 extends, it pushes landing gear 20 downwards, using landing gear 20 to support the aircraft during landing. After the aircraft takes off, the landing gear electric cylinder 21 retracts, pulling the landing gear 20 inward into the mounting slot 2 503, reducing the aircraft's flight drag.

[0042] The turbine engine 2 used in this invention has high thrust efficiency and good performance. The turbine blades of the turbine engine 2 are not exposed, making it safer and longer in service life. The various structures within the aircraft are compact, resulting in low air resistance. It can take off and land vertically, is runway-independent, and offers high flexibility. Air pressure and drag are reduced in front of the aircraft, while air pressure increases at the bottom and decreases in front, facilitating efficient flight. The six-way flow splitting allows the aircraft's direction and attitude to change with thrust, providing a unique control method that eliminates the need for a servo system compared to fixed-wing aircraft.

[0043] For example Figure 1 The aircraft shown features a hexagonal ring wing, allowing it to be combined with other aircraft of the same model. The wings (5) are connected side-to-side, enabling combinations of two, three, four, or seven units to form a larger aircraft, increasing payload and expanding market applications. For example, when assembling seven aircraft modules, the central module connects to six others, specifically by connecting each of the six outermost wings (5) to a wing (5) within one of the aircraft modules, creating a honeycomb-like hexagonal distribution. When assembling into a larger aircraft, the retractable tail and landing gear assemblies between the modules can be removed, leaving only the outermost retractable tail and landing gear assemblies.

[0044] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited thereto. Various changes can be made within the scope of knowledge possessed by those skilled in the art without departing from the spirit of the present invention.

Claims

1. A split jet aircraft characterized by, The jet mechanism sprays air from top to bottom. The shunt cabin (4) is arranged at the bottom of the jet mechanism, has an air inlet channel at the top, and has a plurality of uniformly distributed shunt ports (402) on the outer periphery. The flight control cabin (41) is arranged at the bottom of the shunt cabin (4). The jet control mechanism is uniformly arranged on the periphery of the shunt cabin (4), introduces the air sprayed from the shunt ports (402), controls the air flow range, and sprays the air downward. The retractable tail wing is uniformly arranged on the periphery of the shunt cabin (4). The jet mechanism includes a support cylinder (1), a turbine engine (2), and an oil tank (3). One side of the cross section of the support cylinder (1) is in the shape of an inverted "U". A grid plate (101) is arranged on the inner side of the hollow of the support cylinder (1). The turbine engine (2) is arranged inside the support cylinder (1). The oil tank (3) is arranged at the bottom of the grid plate (101) to supply oil to the turbine engine (2).

2. A split-jet aircraft according to claim 1, wherein, The shunt cabin (4) has a convex flow guide surface (401) in the middle. The flow guide surface (401) guides the air sprayed downward by the jet mechanism to the circumferential shunt ports (402).

3. A split-jet aircraft according to claim 1, wherein, The shunt cabin (4) has a plurality of air outlets (403) arranged in an inclined manner at the lower part. The top end of the air outlet (403) penetrates the flow guide surface (401). The flight control cabin (41) has a heat dissipation port arranged on the periphery.

4. A split-jet aircraft according to claim 3, wherein, The jet control mechanism includes a wing (5), a jet cylinder (6), and a wind port adjusting assembly. The wing (5) and the jet cylinder (6) are both in the shape of a cylinder. The jet cylinder (6) is arranged inside the wing (5). The wing (5) has a mounting port (501) in communication with the shunt port (402). The jet cylinder (6) is hollow inside. The side of the jet cylinder (6) has an air inlet port (601) in communication with the mounting port (501). The inner periphery of the top of the jet cylinder (6) has a circumferential jet port (602) arranged in an inclined downward manner. The wind port adjusting assembly is arranged at the air inlet port (601) of the jet cylinder (6) to control the flow range of the air at the air inlet port (601).

5. A split-jet aircraft according to claim 1, wherein, A grid frame (64) is arranged inside the hollow of the jet cylinder (6). The grid frame (64) has through holes uniformly arranged thereon.

6. A split-jet aircraft according to claim 5, wherein, The wind port adjusting assembly includes an upper plate (71) and a lower plate (72) arranged on the jet cylinder (6), a rack one (12) slidingly arranged on the upper plate (71), a motor (8) arranged on the upper plate (71), and a plurality of wind blocking assemblies arranged side by side. Each wind blocking assembly includes a rotating shaft (9) rotatingly arranged on the upper plate (71) and the lower plate (72), a leaf plate (10) arranged on the rotating shaft (9), and a gear one (11) arranged on the rotating shaft (9) and meshingly connected with the rack one (12). The motor (8) is drivingly connected with one rotating shaft (9).

7. A split-jet aircraft according to claim 5, wherein, The surfaces on both sides of the leaf plate (10) are both in the shape of an arc. Pit grooves (1001) are uniformly arranged on the surfaces.

8. A split-jet aircraft according to claim 7, wherein, The wing (5) has a mounting groove one (502) arranged on the side. The retractable tail wing includes a tail wing (13) and a retractable assembly controlling the linear movement of the tail wing (13).

9. A split-jet aircraft according to claim 5, wherein, The wing (5) has a mounting groove two (503) arranged on the side. A landing gear assembly is arranged at the mounting groove two (503).

10. A split-jet aircraft according to claim 5, wherein, ​

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