Quick connecting device for wing body of aircraft

Abstract

The invention discloses an aircraft wing body quick connecting device, and relates to the field of aircrafts, the aircraft wing body quick connecting device comprises an aircraft body and wings mounted on the two sides of the aircraft body, and insertion rods are fixedly connected to the root positions of the wings; inserting barrels are fixedly connected to the positions, in butt joint with the wings, of the aircraft body, and the inserting rods are matched with the inserting barrels in an inserting mode; the opening area of the insertion cylinder is larger than that of the insertion end of the insertion rod; a clamping assembly is arranged in the machine body and used for automatically clamping the inserting rod into the inserting barrel when the inserting rod is connected with the inserting barrel in an inserted mode. Positioning assemblies are arranged in the wings, and the positioning assemblies are used for fixing the wings at a preset angle relative to the aircraft body after the insertion rods and the insertion barrels are connected in an inserted mode; the wing can be quickly mounted and dismounted, accurate butt joint is not needed during mounting, and operation is convenient.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to a quick-connect device for aircraft wing-body assembly. Background Technology

[0002] When transporting small manned aircraft in no-fly zones and harsh environments, detachable wing designs are often used to facilitate transportation, storage, or meet the modular requirements of specific missions. Currently, wing-body connections mostly rely on precision mechanical interfaces, such as fastening with multiple locating pins and bolts. While this method ensures structural strength, it has significant drawbacks in practice: First, installation requires highly precise alignment between the wing connection components and the fuselage interface. Due to the large size and weight of the wing, specialized tools or multiple people are often required, making the process cumbersome and time-consuming, hindering rapid deployment. Second, the wing's installation angle (or sweep angle) after connection is usually fixed or requires additional complex adjustment mechanisms, making it difficult to reliably lock the wing at a unique and precise preset angle while quickly disassembling and assembling. Furthermore, under vibration or frequent disassembly / assembly conditions, traditional pure bolt connections are prone to loosening, posing safety hazards. Summary of the Invention

[0003] The purpose of this invention is to provide a quick-connect device for aircraft wings and bodies to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a quick-connect device for aircraft wing-body, comprising a fuselage and wings installed on both sides of the fuselage, wherein a plug rod is fixedly connected to the root of the wing; and a plug tube is fixedly connected to the fuselage at the position where it docks with the wing, wherein the plug rod and the plug tube are inserted into each other.

[0005] The size of the opening portion of the insert is much larger than the size of the insertion end portion of the insert rod;

[0006] The machine body is provided with a locking component, which is used to automatically lock the insertion rod into the insertion tube when the insertion rod is inserted into the insertion tube;

[0007] The wing is equipped with a positioning component, which is used to fix the wing relative to the fuselage at a preset angle after the plug rod and the plug tube are inserted.

[0008] Preferably, the engaging assembly includes a chamber I formed within the body, the tail end of the insert being located within the chamber I and fixedly connected to the inner wall of the chamber I; the inner wall of the insert is provided with a plurality of locking blocks, the locking blocks being slidably connected to the insert and penetrating the inner wall of the insert; the surface of the insert rod is provided with an annular groove, the locking blocks engaging with the groove; the chamber I is provided with a driving unit I, the driving unit I being used to simultaneously drive the plurality of locking blocks to slide relative to the insert.

[0009] Preferably, the drive unit includes a drive ring sleeved on the outer surface of the insert, a slide rod fixedly connected to the drive ring, the slide rod being slidably connected to the inner wall of the chamber, and a spring sleeved on the slide rod, one end of the spring being fixedly connected to the drive ring and the other end being fixedly connected to the inner wall of the chamber; the locking block is located inside the chamber and one end is rotatably connected to a connecting rod, which is rotatably connected to the drive ring; the plurality of locking blocks are arranged in a circumferential array relative to the insert.

[0010] Preferably, a cylinder is fixedly connected inside the chamber, and a push plate is fixedly connected to the telescopic end of the cylinder; a connecting plate is fixedly connected to the ends of the two slide rods away from the insert, and the push plate is located between the connecting plate and the insert.

[0011] Preferably, the positioning component includes a second chamber located within the wing. Slide plates are slidably connected to the front and rear ends of the inner wall of the second chamber. A positioning rod is fixedly connected to one end of the slide plate near the fuselage. The positioning rod is slidably connected to and penetrates the inner wall of the second chamber. Positioning slots are provided on the fuselage at the front and rear ends of the insert, and the two positioning rods are respectively inserted into the two positioning slots. A second driving unit is provided within the second chamber, which drives the two positioning rods to be inserted into the two positioning slots respectively.

[0012] Preferably, the second driving unit includes a second sliding rod inserted into the insertion rod, the second sliding rod being slidably connected to the insertion rod and passing through the insertion rod and the inner wall of the second chamber; a driving block is fixedly connected to one end of the second sliding rod inside the second chamber, and connecting rods are symmetrically rotatably connected to the front and rear sides of the driving block, the other end of the connecting rods being rotatably connected to a limiting block, the limiting block being slidably connected to the inner wall of the second chamber; a limiting hole is provided on the sliding plate near the insertion rod, and the limiting block is clearance-fitted with the limiting hole; a second spring and a third spring are respectively sleeved on the second sliding rod and the positioning rod, one end of the second spring being fixedly connected to the driving block and the other end being fixedly connected to the inner wall of the second chamber; one end of the third spring is fixedly connected to the sliding plate and the other end being fixedly connected to the inner wall of the second chamber; a triggering unit is provided inside the insertion cylinder, the triggering unit being used to drive the second sliding rod to move closer to the second chamber when the wing is at a preset angle relative to the fuselage.

[0013] Preferably, the triggering unit includes a slide rod three that is slidably connected to and passes through the insert. One end of the slide rod three is fixedly connected to a spring four inside the chamber one, and the other end of the spring four is fixedly connected to the insert. The slide rod two and the slide rod three are respectively offset from the axis of the insert rod and the insert, and the diameters of the slide rod two and the slide rod three are equal. The elastic force of the spring four is greater than the sum of the elastic forces of the two springs three and the spring two.

[0014] Preferably, a reinforcing plate is provided below the wing root, the reinforcing plate is rotatably connected to the fuselage and has multiple reinforcing grooves; multiple reinforcing blocks are fixedly connected to the wing root, and the multiple reinforcing blocks are respectively engaged with each reinforcing groove; cylinders are rotatably connected to the fuselage at positions before and after the reinforcing plate, and the telescopic ends of the cylinders are rotatably connected to the reinforcing plate; landing gear connected to rollers is installed at the bottom of the fuselage.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] 1. This invention creates a wide-entry guide structure by designing the opening of the insert tube to be significantly larger than the insertion end of the insert rod. This eliminates the need for high-precision visual alignment or fine adjustments during initial docking, allowing the operator to easily guide the wing insert rod into the insert tube, significantly reducing the requirements for the operating environment and technical proficiency. After the insert rod is in place, the locking assembly automatically drives the locking block to engage with the annular groove of the insert rod under the action of a spring, completing the main connection locking. This achieves rapid automation from "alignment" to "locking," making it particularly suitable for scenarios requiring frequent disassembly and assembly or rapid field deployment.

[0017] 2. This invention deeply integrates angle positioning functionality with the main connecting structure. A trigger unit is formed by two off-axis sliding rods, Slide 2 and Slide 3, ensuring that they align only when the wing rotates to a unique preset angle. The trigger positioning rod automatically springs into the fuselage positioning slot under spring pressure, thus precisely locking the wing angle. This design combines angle correction and locking into one, eliminating the need for external measuring tools and ensuring aerodynamic consistency. Furthermore, the added cylinder-driven rotating reinforcing plate and its snap-fit ​​connection with the reinforcing block provide a first-level redundant reinforcement on top of the core insertion and locking mechanism. This effectively distributes and withstands alternating loads during flight, significantly improving the fatigue and impact resistance of the overall connection and ensuring safety and reliability under high-stress flight conditions. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0019] Figure 2 This is a bottom-view structural diagram of the present invention;

[0020] Figure 3 A schematic diagram of the disassembled structure of this invention;

[0021] Figure 4 This is a schematic diagram of the insert rod in this invention;

[0022] Figure 5 This is a cross-sectional view of the wing structure in this invention;

[0023] Figure 6 for Figure 5 A magnified structural diagram of A in the middle;

[0024] Figure 7 This is a partial cross-sectional view of the body in this invention;

[0025] Figure 8 This is a schematic diagram of the insert structure in this invention;

[0026] Figure 9 This is a cross-sectional view of the insert in this invention;

[0027] Figure 10 This is a schematic diagram of the reinforcing plate in this invention;

[0028] Figure 11 This is a schematic diagram of the insertion rod engagement principle in this invention;

[0029] Figure 12 This is a schematic diagram illustrating the connection principle of slide bar two and slide bar three in this invention.

[0030] In the attached diagram, the components represented by each number are as follows:

[0031] 1. Airframe; 2. Wing; 3. Insert rod; 4. Insert cylinder; 5. Chamber 1; 6. Locking block; 7. Locking slot; 8. Drive ring; 9. Slide rod 1; 10. Spring 1; 11. Connecting rod 1; 12. Chamber door; 13. Push plate; 14. Chamber 2; 15. Slide plate; 16. Positioning rod; 17. Positioning groove; 18. Slide rod 2; 19. Drive block; 20. Connecting rod 2; 21. Limiting block; 22. Limiting hole; 23. Spring 2; 24. Spring 3; 25. Slide rod 3; 26. Spring 4; 27. Cylinder 1; 28. Connecting plate; 29. ​​Reinforcing plate; 30. Reinforcing groove; 31. Reinforcing block; 32. Cylinder 2; 33. Landing gear. Detailed Implementation

[0032] Please see Figures 1-12 The present invention provides a technical solution: a quick connection device for aircraft wing body, including a fuselage 1 and wings 2 installed on both sides of the fuselage 1, with a plug rod 3 fixedly connected to the root of the wing 2; a plug tube 4 is fixedly connected to the fuselage 1 at the docking position with the wing 2, and the plug rod 3 and the plug tube 4 are plugged into each other.

[0033] The size of the opening portion of the insert 4 is much larger than the size of the insertion end portion of the insert rod 3;

[0034] The body 1 is equipped with a locking component, which is used to automatically lock the insertion rod 3 into the insertion tube 4 when the insertion rod 3 is inserted into the insertion tube 4;

[0035] The wing 2 is equipped with a positioning component inside. The positioning component is used to fix the wing 2 relative to the fuselage 1 at a preset angle after the plug rod 3 and the plug tube 4 are plugged in.

[0036] During work ( Figure 1 (x, y, and z represent the front, right, and top sides, respectively). Insert the rod 3 of the docking part of the wing 2 into the tube 4 installed on the fuselage 1. Since the area of ​​the opening part of the tube 4 is larger than the area of ​​the insertion end of the rod 3, the rod 3 can be easily inserted into the tube 4 without the need to closely adjust the position of the wing 2, which can effectively improve the convenience of docking the wing 2.

[0037] After the insertion rod 3 is fully inserted into the insertion cylinder 4, the locking component inside the fuselage 1 will automatically lock the insertion rod 3 into the insertion cylinder 4, which can maintain the docking state between the wing 2 and the fuselage 1.

[0038] When the insertion rod 3 is inserted into the insertion cylinder 4, the wing 2 is rotated to cause the wing 2 to rotate relative to the body 1. When the wing 2 rotates relative to the body 1 to a preset angle, the positioning component fixes the angle of the wing 2 relative to the body 1. Under the combined action of the locking component and the positioning component, the wing 2 can be stably fixed on the body 1.

[0039] See Figures 3-6 , Figure 9 As a further embodiment of the present invention, the engaging assembly includes a chamber 5 formed within the body 1, with the tail of the insert 4 located within the chamber 5 and fixedly connected to the inner wall of the chamber 5; the inner wall of the insert 4 is provided with a plurality of locking blocks 6, which are slidably connected to the insert 4 and penetrate the inner wall of the insert 4; the surface of the insert rod 3 is provided with an annular groove 7, and the locking blocks 6 engage with the groove 7; a driving unit is provided within the chamber 5, which is used to simultaneously drive a plurality of locking blocks 6 to slide relative to the insert 4;

[0040] The drive unit includes a drive ring 8 sleeved on the outer surface of the insert 4. A slide rod 9 is fixedly connected to the drive ring 8. The slide rod 9 is slidably connected to the inner wall of the chamber 5, and a spring 10 is sleeved on the slide rod 9. One end of the spring 10 is fixedly connected to the drive ring 8, and the other end is fixedly connected to the inner wall of the chamber 5. A locking block 6 is located inside the chamber 5, and one end is rotatably connected to a connecting rod 11. The connecting rod 11 is rotatably connected to the drive ring 8. Multiple locking blocks are arranged in a circumferential array relative to the insert 4.

[0041] During operation, after inserting the rod 3 into the insert cylinder 4, the inclined portion of the rod 3 in the forward direction contacts the locking block 6, which then pushes the locking block 6 into the chamber 5. The locking block 6 begins to slide relative to the insert cylinder 4 and drives the drive ring 8 to move in the forward direction of the rod 3 via the connecting rod 11. When the rod 3 is fully inserted into the insert cylinder 4, the slot 7 on the surface of the rod 3 moves to the position where it engages with the locking block 6. Under the action of the spring 10, the drive ring 8 drives the locking block 6 directly into the slot 7 via the connecting rod 11. At this time, under the action of the locking block 6, the rod 3 cannot be withdrawn from the insert cylinder 4. At the same time, since the slot 7 is annular, the rod 3 can rotate normally inside the insert cylinder 4.

[0042] See Figures 6-7 As a further embodiment of the present invention, a cylinder 27 is fixedly connected inside the chamber 5, and a push plate 13 is fixedly connected to the telescopic end of the cylinder 27; a connecting plate 28 is fixedly connected to the ends of the two slide rods 9 away from the insert 4, and the push plate 13 is located between the connecting plate 28 and the insert 4.

[0043] During operation, when it is necessary to disassemble the wing 2, the cylinder 27 is started to retract. When the cylinder 27 retracts, it drives the push plate 13 to move away from the insert 4. After the push plate 13 moves to the position where it is in contact with the connecting plate 28, it starts to drive the connecting plate 28 to move. The connecting plate 28 drives the two slide rods 9 to move. The two slide rods 9 drive the drive ring 8 to move. The drive ring 8 then drives the locking block 6 to disengage from the locking groove 7 through the connecting rod 11. At this time, the wing 2 can be removed from the fuselage 1.

[0044] See Figures 5-6 , Figures 11-12 As a further embodiment of the present invention, the positioning assembly includes a second chamber 14 formed within the wing 2. Slide plates 15 are slidably connected to the front and rear positions of the inner wall of the second chamber 14. A positioning rod 16 is fixedly connected to one end of the slide plate 15 near the fuselage 1. The positioning rod 16 is slidably connected to and penetrates the inner wall of the second chamber 14. Positioning slots 17 are formed on the fuselage 1 at the front and rear positions of the insert 4. The two positioning rods 16 are respectively inserted into the two positioning slots 17. A second driving unit is provided within the second chamber, which drives the two positioning rods 16 to be inserted into the two positioning slots 17 respectively.

[0045] Drive unit two includes a slide rod two 18 inserted into the insertion rod 3, slide rod two 18 being slidably connected to the insertion rod 3 and passing through the insertion rod 3 and the inner wall of chamber two 14; one end of slide rod two 18 is fixedly connected to a drive block 19 inside chamber two 14, and connecting rod two 20 is symmetrically rotatably connected to the front and rear sides of drive block 19, and the other end of connecting rod two 20 is rotatably connected to a limit block 21, the limit block 21 being slidably connected to the inner wall of chamber two 14; a limit hole 22 is opened on the slide plate 15 near the insertion rod 3, limiting... Positioning block 21 is clearance-fitted with limiting hole 22; spring 23 and spring 3 24 are respectively sleeved on slide rod 28 and positioning rod 16, one end of spring 23 is fixedly connected to drive block 19 and the other end is fixedly connected to inner wall of chamber 2 14; one end of spring 3 24 is fixedly connected to slide plate 15 and the other end is fixedly connected to inner wall of chamber 2 14; a triggering unit is provided in insert 4, which is used to drive slide rod 2 18 to move closer to chamber 2 14 when wing 2 is at a preset angle relative to body 1;

[0046] The triggering unit includes a slide rod 25 that is slidably connected to and passes through the insert 4. One end of the slide rod 25 is fixedly connected to a spring 26 inside the chamber 5, and the other end of the spring 26 is fixedly connected to the insert 4. The slide rods 28 and 25 are respectively offset from the axes of the insert rod 3 and the insert 4, and the diameters of the slide rods 28 and 25 are equal. The elastic force of the spring 26 is greater than the sum of the elastic forces of the two springs 24 and the spring 23.

[0047] During operation, when the insertion rod 3 is inserted into the insertion cylinder 4, because the sliding rods 25 and 18 are respectively off-axis from the insertion cylinder 4 and the insertion rod 3, the sliding rods 25 and 18 are basically not in a straight line. When the insertion rod 3 is inserted into the insertion cylinder 4, the insertion end of the insertion rod 3 contacts the sliding rod 25, which pushes the sliding rod 25 into the chamber 5. When the insertion rod 3 is fully inserted into the insertion cylinder 4, the wing 2 begins to rotate, and the wing 2 drives the insertion rod 3 to rotate. When the wing 2 rotates to the preset angle, the sliding rods 25 and 18... 5 are exactly on the same straight line. At this time, slide bar 3 25 pushes slide bar 2 18 into chamber 2 14 under the action of spring 4 26. Slide bar 2 18 then drives drive block 19 to move. Drive block 19 drives limit block 21 to exit from limit hole 22 through connecting rod 2 20. After limit block 21 exits from limit hole 22, positioning rod 16 extends out from chamber 2 14 under the action of spring 3 24. The two extended positioning rods 16 are inserted into the two positioning slots 17 on the fuselage 1 respectively. At this time, the angle between wing 2 and fuselage 1 is fixed.

[0048] Under the action of spring 26, when it is necessary to disassemble the wing 2, the two push plates 13 are pinched by hand and driven to move, so that the insertion rod 3 is separated from the insertion cylinder 4. At this time, spring 26 can automatically pop the insertion rod 3 out of the insertion cylinder 4.

[0049] See Figures 2-4 , Figure 10 As a further embodiment of the present invention, a reinforcing plate 29 is provided below the root of the wing 2. The reinforcing plate is rotatably connected to the fuselage 1 and has multiple reinforcing grooves 30. Multiple reinforcing blocks 31 are fixedly connected to the root of the wing 2, and the multiple reinforcing blocks 31 are respectively engaged with each reinforcing groove 30. Cylinders 32 are rotatably connected to the fuselage 1 at the front and rear positions of the reinforcing plate 29. The telescopic ends of the cylinders 32 are rotatably connected to the reinforcing plate 29. A landing gear 33 connected to rollers is installed at the bottom of the fuselage 1.

[0050] During operation, after the wing 2 is correctly positioned and angled to mate with the fuselage 1, the cylinders 32 on both the front and rear sides can be simultaneously retracted. As the cylinders 32 retract, they cause the reinforcing plate 31 to rotate upwards. When the reinforcing plate 31 rotates to a position where it is in contact with the fuselage 1 and the wing 2, the cylinders 32 on both the front and rear sides stop. The multiple reinforcing blocks 31 on the wing 2 are then fully engaged in the multiple reinforcing grooves 30 on the reinforcing plate 29. The reinforcing plate 29 further enhances the tightness of the connection between the wing 2 and the fuselage 1. It should be noted that this reinforcement method is not the only one. In response to different flight environments, after the wing 2 is quickly mated with the fuselage 1, other appropriate reinforcement methods can be selected according to the flight environment to ensure flight safety.

Claims

1. A quick-connect device for aircraft wing-body assembly, comprising a fuselage (1) and a wing (2), characterized in that: A plug rod (3) is fixedly connected to the root of the wing (2); the fuselage (1) is provided with a plug tube (4) for docking the plug rod (3); The body (1) is provided with a locking assembly, which is used to lock the insert rod (3) into the insert tube (4) from a direction perpendicular to the axis of the insert rod (3) when the insert rod (3) is inserted into the insert tube (4) to a preset depth; The wing (2) is provided with a positioning component inside. The positioning component is used to fix the wing (2) relative to the body (1) at a preset angle after the plug rod (3) and the plug tube (4) are plugged in.

2. The aircraft wing-body quick-connection device according to claim 1, characterized in that: The locking assembly includes a chamber (5) opened in the body (1); the inner wall of the insert (4) is provided with a number of locking blocks (6); the surface of the insert rod (3) is provided with a slot (7), and the multiple locking blocks (6) are engaged with the slot (7); the chamber (5) is provided with a drive unit, which is used to drive the multiple locking blocks (6) to slide relative to the insert (4) at the same time.

3. The aircraft wing-body quick-connection device according to claim 2, characterized in that: The tail of the insert (4) is located inside the first chamber (5) and the insert (4) is fixedly connected to the inner wall of the first chamber (5); the block (6) is slidably connected to the insert (4) and penetrates the inner wall of the insert (4); the slot (7) is annular in shape.

4. The aircraft wing-body quick-connection device according to claim 2, characterized in that: The drive unit includes a drive ring (8) sleeved on the outer surface of the insert (4), a slide rod (9) fixedly connected to the drive ring (8), the slide rod (9) being slidably connected to the inner wall of the chamber (5) and a spring (10) sleeved on the slide rod (9), one end of the spring (10) being fixedly connected to the drive ring (8) and the other end being fixedly connected to the inner wall of the chamber (5); the locking block (6) is located inside the chamber (5) and one end is rotatably connected to a connecting rod (11), the connecting rod (11) being rotatably connected to the drive ring (8); the multiple locking blocks (6) are arranged in a circumferential array relative to the insert (4).

5. The aircraft wing-body quick-connection device according to claim 4, characterized in that: A cylinder (27) is fixedly connected inside the chamber (5), and a push plate (13) is fixedly connected to the telescopic end of the cylinder (27); a connecting plate (28) is fixedly connected to the ends of the two slide rods (9) away from the insert (4), and the push plate (13) is located between the connecting plate (28) and the insert (4).

6. The aircraft wing-body quick-connection device according to claim 1, characterized in that: The positioning assembly includes a second chamber (14) located inside the wing (2). Slide plates (15) are slidably connected to the front and rear positions of the inner wall of the second chamber (14). A positioning rod (16) is fixedly connected to the end of the slide plate (15) near the body (1). The positioning rod (16) is slidably connected to the inner wall of the second chamber (14) and penetrates the inner wall of the second chamber (14). Positioning slots (17) are provided on the body (1) at the front and rear positions of the insert (4). The two positioning rods (16) are respectively inserted into the two positioning slots (17). A second driving unit is provided inside the second chamber (14). The second driving unit is used to drive the two positioning rods (16) to be inserted into the two positioning slots (17).

7. The aircraft wing-body quick-connection device according to claim 6, characterized in that: The second drive unit includes a second slide rod (18) inserted into the insert rod (3). The second slide rod (18) is slidably connected to the insert rod (3) and passes through the insert rod (3) and the inner wall of the second chamber (14). One end of the second slide rod (18) is fixedly connected to a drive block (19) inside the second chamber (14). The front and rear sides of the drive block (19) are symmetrically connected to a second connecting rod (20). The other end of the second connecting rod (20) is rotatably connected to a limit block (21). The slide is slidably connected to the inner wall of the second chamber (14); a limiting hole (22) is provided on the slide plate (15) near the insertion rod (3), and the limiting block (21) is in clearance fit with the limiting hole (22); a spring three (24) is sleeved on the positioning rod (16), one end of the spring three (24) is fixedly connected to the slide plate (15) and the other end is fixedly connected to the inner wall of the second chamber (14); a release unit is provided inside the wing, and the release unit is used to drive the limiting block (21) to release from the limiting hole (22).

8. The aircraft wing-body quick-connection device according to claim 7, characterized in that: The disengagement unit includes a spring (23) sleeved on the slide bar (18). One end of the spring (23) is fixedly connected to the drive block (19) and the other end is fixedly connected to the inner wall of the chamber (14). The insert (4) is provided with a triggering unit, which is used to drive the slide bar (18) to move closer to the chamber (14) when the wing (2) is at a preset angle relative to the body (1).

9. The aircraft wing-body quick-connection device according to claim 8, characterized in that: The triggering unit includes a slide rod three (25) that is slidably connected to and passes through the insert (4). The slide rod three (25) is located in the first chamber (5) and one end is fixedly connected to a spring four (26). The other end of the spring four (26) is fixedly connected to the insert (4). The slide rod two (18) and the slide rod three (25) are respectively offset from the axis of the insert rod (3) and the insert (4), and the diameters of the slide rod two (18) and the slide rod three (25) are equal. The elastic force of the spring four (26) is greater than the sum of the elastic forces of the two spring three (24) and the spring two (23).

10. The aircraft wing-body quick-connection device according to claim 1, characterized in that: A reinforcing plate (29) is provided below the root of the wing (2). The reinforcing plate is rotatably connected to the fuselage (1) and has multiple reinforcing grooves (30) on it. Multiple reinforcing blocks (31) are fixedly connected to the root of the wing (2). The multiple reinforcing blocks (31) are respectively engaged with each reinforcing groove (30). Cylinders (32) are rotatably connected to the fuselage (1) at the front and rear positions of the reinforcing plate (29). The telescopic ends of the cylinders (32) are rotatably connected to the reinforcing plate (29). A landing gear (33) connected to rollers is installed at the bottom of the fuselage (1).

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