A rapid connection device for the wing and fuselage of an aircraft

Abstract

The present application discloses a rapid wing-body connection device for an aircraft. Both ends of at least one guide rod are respectively connected to adjacent beams within the wing surface; the first docking seat and the second docking seat are respectively slidably connected to both sides of the guide rod and are located inside the adjacent beams within the wing surface; both the first docking seat and the second docking seat are provided with locking holes; one ends of at least two locking mechanisms respectively pass through the corresponding locking holes and extend into the corresponding first docking seat and second docking seat; the limiting frame of the fuselage is provided with limiting holes corresponding to the locking holes; both ends of the first tension member respectively extend into the first docking seat and the second docking seat and are connected to the corresponding locking mechanisms; both ends of the second tension member are respectively connected to the first docking seat and the second docking seat; the hook mechanism is connected to the first tension member and the second tension member. By the rapid action of the hook mechanism in the present application, the first tension member and the second tension member are pulled to realize the extension and retraction of the locking mechanisms, thereby shortening the connection and disassembly time of the wing and the fuselage.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and particularly to a rapid connection device for the wing and fuselage of an aircraft. Background Art

[0002] An aircraft is an unmanned aerial vehicle that is controlled by a radio remote control device and a self - contained program control device, and is usually equipped with various advanced technical devices such as an autopilot and a program control device. Ground operators can track, position, remotely control, remotely measure, and transmit digital information of the aircraft through devices such as radar and positioning systems. Therefore, aircraft have been widely used in many fields such as aerial reconnaissance, surveillance, communication, anti - submarine, and electronic jamming.

[0003] For a detachable aircraft, its fuselage, wings, and tail can be disassembled, which is convenient for storage and transportation. Currently, the wings or tail are mostly connected to the fuselage by bolts. However, this connection method not only requires sufficient space to complete the installation and disassembly operations of the bolts, thus occupying a relatively large space, but also the installation and disassembly process of the bolts requires manual operation, which is time - consuming and labor - intensive. Summary of the Invention

[0004] By providing a rapid connection device for the wing and fuselage of an aircraft in an embodiment of the present application, the technical problem in the prior art that the wings or tail of an aircraft are connected to the fuselage by bolts, which requires sufficient space for installers to install and disassemble the bolts, occupies a large space, and the disassembly and assembly of bolts are time - consuming and labor - intensive is solved.

[0005] The embodiment of the present application provides an aircraft wing-body quick connection device, comprising a first docking seat, a second docking seat, a locking hook mechanism, a first stretching member, a second stretching member, at least one guide rod and at least two locking mechanisms; at least one of the two ends of the guide rod is respectively connected to adjacent beams in the wing surface; the first docking seat and the second docking seat are respectively slidably connected to the two sides of the guide rod, and are located on the inner side of the adjacent beams in the wing surface, and are configured to be inserted into the corresponding limit frame of the fuselage; the first docking seat and the second docking seat are both provided with locking holes; one end of at least two of the locking mechanisms passes through the corresponding locking holes and extends into the corresponding first docking seat and the second docking seat; The limiting frame of the fuselage is provided with a limiting hole corresponding to the locking hole; the two ends of the first stretching member respectively extend into the first docking seat and the second docking seat, and are connected to the corresponding locking mechanism; the two ends of the second stretching member are respectively connected to the first docking seat and the second docking seat; the locking hook mechanism is connected to the first stretching member and the second stretching member, and is configured to pull the first stretching member and the second stretching member so that the first stretching member drives the locking mechanism located outside the locking hole to extend into the corresponding first docking seat and the second docking seat, and at the same time, the second stretching member drives the first docking seat and the second docking seat to move in a direction close to each other.

[0006] In a possible implementation, the first stretching member includes a rope, two reset elastic members and two baffles; the two reset elastic members and the two baffles are respectively located in the first docking seat and the second docking seat; the two ends of the rope extend into the first docking seat and the second docking seat respectively, and pass through the corresponding baffles to be connected to the corresponding locking mechanism; one end of the two reset elastic members is fixed to the side of the corresponding baffle facing the locking mechanism, and the other end thereof is abutted against the corresponding locking mechanism.

[0007] In one possible implementation, the aircraft wing-body quick connection device also includes two support guide seats; the two support guide seats are respectively fixedly connected to the first docking seat and the second docking seat, and are located on the side of the baffle away from the locking mechanism; after the two ends of the rope extend into the first docking seat and the second docking seat, they bypass the corresponding support guide seats, and the support guide seats are configured to guide the rope through the corresponding baffle.

[0008] In a possible implementation, the locking mechanism includes a slider, a tension spring, and two locking pins; the slider and the tension spring are disposed in both the first docking seat and the second docking seat; both ends of the first stretching member are respectively connected to the corresponding slider; the slider is of a hollow structure; both ends of the tension spring respectively pass through the top wall and the bottom wall of the slider and are connected to the two locking pins, and both sides of the tension spring abut against the top wall and the bottom wall of the slider; the longitudinal section of one side of the slider away from the first stretching member is of a triangular structure; one end of the two locking pins away from the tension spring partially extends out of the corresponding locking hole, and one side of the two locking pins close to the tension spring is slidably connected to the top surface and the bottom surface of one side of the slider away from the first stretching member.

[0009] In a possible implementation, the locking mechanism further includes a guide post; the two locking pins are slidably connected to both sides of the guide post; the tension spring is sleeved on the outer wall of the guide post; corresponding chutes are disposed on both the top surface and the bottom surface of one side of the slider away from the first stretching member and corresponding to the guide post.

[0010] In a possible implementation, the aircraft wing-body quick connection device further includes at least one compression spring; at least one compression spring is disposed between the first docking seat and the second docking seat and is configured to limit the distance between the first docking seat and the second docking seat.

[0011] In a possible implementation, the locking hook mechanism includes a first lock housing, a second lock housing, a limit seat, a pull-lock hook, and a connecting rod; the first lock housing is disposed on the skin of the fuselage; the second lock housing is disposed on the skin of the wing surface and corresponds to the first lock housing; the first lock housing and the second lock housing are located between the first docking seat and the second docking seat; the limit seat is disposed on the first lock housing; a through hole is disposed on one side of the second lock housing away from the first lock housing, and one end of the connecting rod passes through the through hole; connection holes for the first stretching member and the second stretching member to pass through are disposed at intervals along the height direction of the connecting rod; one end of the pull-lock hook is rotatably connected to one side of the connecting rod away from the connection hole and is configured to pull the connecting rod to move when the included angle with the second lock housing is 90°; the other end of the pull-lock hook is a free end and is configured to be inserted into the limit seat.

[0012] In a possible implementation, the material of the pull-lock hook is hard rubber; the limit seat is of a U-shaped structure, and the opening width at the top of the U-shaped structure is smaller than the opening width at the bottom.

[0013] In a possible implementation, the hook mechanism further includes a lock cover; the lock cover is hinged to one end of the second lock housing away from the first lock housing, and a spring bolt is provided on a side of the lock cover away from the second lock housing; a socket corresponding to the spring bolt is provided on a side of the second lock housing away from the first lock housing.

[0014] In a possible implementation, the longitudinal cross-sections of the first docking seat and the second docking seat are both of a first trapezoidal structure; the longitudinal cross-section of the limiting frame of the fuselage is a second trapezoidal structure corresponding to the first trapezoidal structure.

[0015] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0016] The aircraft wing-body quick connection device provided in the embodiments of the present application includes a first docking seat, a second docking seat, a hook mechanism, a first tension member, a second tension member, at least one guide rod, and at least two locking mechanisms. When it is necessary to connect the wing and the body, the hook mechanism is activated to start pulling the first tension member and the second tension member. As the first tension member moves, it drives the locking mechanism originally located outside the locking hole to extend into the corresponding first docking seat and second docking seat. At the same time, the second tension member is pulled to drive the first docking seat and the second docking seat to smoothly move along the guide rod in a direction approaching each other. When they move to a predetermined position, the first docking seat and the second docking seat are respectively accurately inserted into the corresponding limiting frames of the fuselage. At this time, the hook mechanism is released, and the locking mechanism returns to its initial position under the action of the first tension member and extends into the limiting holes of the fuselage limiting frame to complete the locking, realizing a firm connection between the wing and the body. When it is necessary to disassemble the wing and the body, the hook mechanism is activated again to pull the first tension member and the second tension member, and the locking mechanism withdraws from the limiting hole and extends into the first docking seat and the second docking seat to release the locking of them. As the first docking seat and the second docking seat completely move out of the limiting frame of the fuselage, the entire aircraft wing-body quick connection device can be easily disassembled from the aircraft to complete the disassembly process. Therefore, through the rapid action of the hook mechanism in the present application, the first tension member and the second tension member can be efficiently pulled, the extension and withdrawal of the locking mechanism, and the smooth movement of the first docking seat and the second docking seat can be realized, thereby reducing unnecessary installation space and shortening the connection and disassembly time of the wing and the body. Description of the Drawings

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for description in the embodiments of the present application. Obviously, the drawings in the following description are some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 Schematic structural diagram of the aircraft wing-body quick connection device provided by the embodiment of the present application;

[0019] Figure 2 Schematic structural diagram of the limit frame provided by the embodiment of the present application;

[0020] Figure 3 Schematic structural diagram of the first docking seat and the second docking seat provided by the embodiment of the present application;

[0021] Figure 4 is Figure 3 Cross-sectional view taken along line B-B in

[0022] Figure 5 is Figure 4 Cross-sectional view taken along line C-C in

[0023] Figure 6 is Figure 5 Cross-sectional view taken along line D-D in

[0024] Figure 7 Schematic structural diagram of the guide rod provided by the embodiment of the present application;

[0025] Figure 8 is Figure 3 Cross-sectional view taken along line F-F of

[0026] Figure 9 Schematic structural diagram of the spring bolt provided by the embodiment of the present application;

[0027] Figure 10 Schematic structural diagram of the locking hook mechanism provided by the embodiment of the present application;

[0028] Figure 11 is Figure 10 Enlarged view at position A of

[0029] Figure 12 Schematic structural diagram of the pin seat provided by the embodiment of the present application;

[0030] Figure 13 Schematic structural diagram of the lock cover provided by the embodiment of the present application;

[0031] Figure 14 Schematic structural diagram of the limit seat provided by the embodiment of the present application;

[0032] Figure 15 Schematic structural diagram of the fuselage and the wing surface provided by the embodiment of the present application;

[0033] Figure 16 Schematic structural diagram of the locking mechanism provided by the embodiment of the present application.

[0034] Icons: 1 - First docking base; 2 - Second docking base; 3 - Hook mechanism; 31 - First lock housing; 32 - Second lock housing; 33 - Limit seat; 331 - U-shaped structure; 34 - Latching hook; 35 - Link; 36 - Lock cover; 361 - Spring bolt; 37 - Pin seat; 4 - Second tension member; 5 - First tension member; 51 - Rope; 52 - Reset elastic member; 53 - Baffle; 6 - Guide rod; 7 - Locking mechanism; 71 - Slide block; 72 - Tension spring; 73 - Locking pin; 74 - Guide post; 8 - Limit frame; 81 - Limit hole; 9 - Support guide seat; 10 - Compression spring; 11 - Airframe; 12 - Wing surface; 13 - Beam. Detailed implementation manner

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present application with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the protection scope of the present application.

[0036] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present application. The terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance. In addition, the terms "installation", "connection", "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0037] The embodiments of the present application provide a rapid connection device for an aircraft wing and fuselage, as Figures 1 to 16As shown in the figure. The quick connection device for the wing and fuselage of the aircraft includes a first docking seat 1, a second docking seat 2, a locking hook mechanism 3, a first tension member 5, a second tension member 4, at least one guide rod 6 and at least two locking mechanisms 7. Both ends of at least one guide rod 6 are respectively connected to adjacent beams 13 within the wing surface 12. The first docking seat 1 and the second docking seat 2 are respectively slidably connected to both sides of the guide rod 6 and are located inside the adjacent beams 13 within the wing surface 12, and are configured to be inserted into the corresponding limit frames 8 of the fuselage 11. The first docking seat 1 and the second docking seat 2 are both provided with locking holes. One end of at least two locking mechanisms 7 passes through the corresponding locking holes and extends into the corresponding first docking seat 1 and second docking seat 2. The limit frame 8 of the fuselage 11 is provided with limit holes 81 corresponding to the locking holes. Both ends of the first tension member 5 respectively extend into the first docking seat 1 and the second docking seat 2 and are connected to the corresponding locking mechanisms 7. Both ends of the second tension member 4 are respectively connected to the first docking seat 1 and the second docking seat 2. The locking hook mechanism 3 is connected to the first tension member 5 and the second tension member 4 and is configured to pull the first tension member 5 and the second tension member 4, so that the first tension member 5 drives the locking mechanism 7 located outside the locking hole to extend into the corresponding first docking seat 1 and second docking seat 2, and at the same time the second tension member 4 drives the first docking seat 1 and the second docking seat 2 to move towards each other.

[0038] In the embodiment of the present application, the wing surface 12 is a tail wing. In the present application, the number of guide rods 6 is two, and the two guide rods 6 are symmetrically arranged on both sides of the second tension member 4. Similarly, the number of locking mechanisms 7 is also two.

[0039] It should be noted that when the wing and the fuselage need to be connected, the hook mechanism 3 is activated to start pulling the first tension member 5 and the second tension member 4. As the first tension member 5 moves, it drives the locking mechanism 7 that was originally outside the locking hole to extend into the corresponding first docking seat 1 and second docking seat 2. At the same time, the second tension member 4 is pulled, driving the first docking seat 1 and the second docking seat 2 to smoothly move along the guide rod 6 in the direction of approaching each other. When they move to the predetermined position, the first docking seat 1 and the second docking seat 2 are respectively inserted into the corresponding limiting frames 8 of the fuselage 11. At this time, the hook mechanism 3 is released, and the locking mechanism 7 returns to the initial position under the action of the first tension member 5 and extends into the limiting hole 81 of the limiting frame 8 of the fuselage 11 to complete the locking and achieve a firm connection between the wing and the fuselage. When the wing and the fuselage need to be disassembled, the hook mechanism 3 is activated again to pull the first tension member 5 and the second tension member 4, and the locking mechanism 7 withdraws from the limiting hole 81 and extends into the first docking seat 1 and the second docking seat 2 to release the locking of them. As the first docking seat 1 and the second docking seat 2 are completely removed from the limiting frame 8 of the fuselage 11, the entire quick connection device of the aircraft wing and fuselage can be easily disassembled from the aircraft to complete the disassembly process. Therefore, through the rapid action of the hook mechanism 3 in this application, the first tension member 5 and the second tension member 4 can be efficiently pulled, the extension and withdrawal of the locking mechanism 7 can be realized, and the smooth movement of the first docking seat 1 and the second docking seat 2 can be achieved, thereby reducing unnecessary installation space and shortening the connection and disassembly time of the wing and the fuselage.

[0040] In the embodiment of this application, the first tension member 5 includes a rope 51, two reset elastic members 52, and two baffles 53. The two reset elastic members 52 and the two baffles 53 are respectively located in the first docking seat 1 and the second docking seat 2. Both ends of the rope 51 extend into the first docking seat 1 and the second docking seat 2 respectively, and pass through the corresponding baffles 53 to be connected to the corresponding locking mechanisms 7. One end of each of the two reset elastic members 52 is fixed to the side of the corresponding baffle 53 facing the locking mechanism 7, and the other end of each of them abuts against the corresponding locking mechanism 7.

[0041] It should be noted that the baffle 53 plays a role in guiding and fixing the reset elastic member 52, and the end face of the reset elastic member 52 away from the locking mechanism 7 must be firmly clamped to avoid loosening.

[0042] When the hook mechanism 3 pulls the rope 51, both ends of the rope 51 will drive the locking mechanisms 7 in the first docking seat 1 and the second docking seat 2 to move towards the baffle 53. In this process, the pulling force of the rope 51 will be transmitted to the reset elastic member 52 through the locking mechanism 7, causing the reset elastic member 52 to be in a compressed state. When the rope 51 is not stressed, the reset elastic member 52 will use its elastic potential energy to push the locking mechanism 7 back to the initial position.

[0043] In the embodiment of the present application, the aircraft wing-body quick connection device further includes two support and guide seats 9. The two support and guide seats 9 are respectively fixedly connected inside the first docking seat 1 and the second docking seat 2, and are located on the side of the baffle 53 away from the locking mechanism 7. After both ends of the rope 51 extend into the first docking seat 1 and the second docking seat 2 respectively, they bypass the corresponding support and guide seats 9, and the support and guide seats 9 are configured to guide the rope 51 to pass through the corresponding baffle 53.

[0044] It should be noted that the support and guide seat 9 plays an important guiding role in the turning of the rope 51 here, ensuring that the rope 51 can move along a predetermined path inside the first docking seat 1 and the second docking seat 2, thereby improving the reliability and stability of the aircraft wing-body quick connection device.

[0045] In the embodiment of the present application, the locking mechanism 7 includes a slider 71, a tension spring 72 and two locking pins 73. The slider 71 and the tension spring 72 are arranged inside both the first docking seat 1 and the second docking seat 2. Both ends of the first tension member 5 are respectively connected to the corresponding slider 71. The slider 71 is of a hollow structure. Both ends of the tension spring 72 pass through the top wall and the bottom wall of the slider 71 respectively and are connected to the two locking pins 73, and both sides of the tension spring 72 abut against the top wall and the bottom wall of the slider 71. The longitudinal section of the side of the slider 71 away from the first tension member 5 is a triangular structure. One end of the two locking pins 73 away from the tension spring 72 partially extends out of the corresponding locking holes, and one side of the two locking pins 73 close to the tension spring 72 is slidably connected to the top surface and the bottom surface of the side of the slider 71 away from the first tension member 5.

[0046] Specifically, one end of the locking pin 73 close to the tension spring 72 is designed as an inclined surface, and the slope of this inclined surface is exactly matched with the slope of the edge of the triangular structure of the slider 71. This design ensures that when the locking pin 73 is subjected to the pulling force of the tension spring 72, it can slide more smoothly and stably along the inclined surface of the slider 71, thereby realizing reliable locking and unlocking functions.

[0047] It should be noted that the slider 71 is designed as a hollow structure to accommodate the tension spring 72. The tension spring 72 is of a double-hook design, and both ends of it are respectively hung on the two locking pins 73, and both sides of the tension spring 72 always keep in contact with the top wall and the bottom wall of the slider 71. Two locking holes are respectively provided on the first docking seat 1 and the second docking seat 2.

[0048] When the first stretching member 5 is pulled, it will drive the corresponding slider 71 to move away from the fuselage 11 in the first docking seat 1 or the second docking seat 2. Since the longitudinal section of the side of the slider 71 away from the first stretching member 5 is a triangular structure, this enables the slider 71 to compress the tension spring 72 during the sliding process, and further enables the four locking pins 73 to extend into the corresponding locking holes respectively. When the first stretching member 5 is not pulled, the slider 71 will move towards the fuselage 11 under the action of the resilience of the first stretching member 5. At this time, the tension spring 72 gradually returns to its initial state and drives the locking pin 73 back to the initial position.

[0049] In the embodiment of the present application, the locking mechanism 7 further includes a guide post 74. Two locking pins 73 are slidably connected to both sides of the guide post 74. The tension spring 72 is sleeved on the outer wall of the guide post 74. The top surface and the bottom surface of the side of the slider 71 away from the first stretching member 5 are both provided with chutes corresponding to the guide post 74.

[0050] It should be noted that the guide post 74 can ensure that the two locking pins 73 do not deviate during the process of extending into or out of the locking holes, thereby ensuring the stability and reliability of the connection.

[0051] Specifically, in order to effectively prevent the locking pin 73 from rotating during operation, the cross-section of the guide post 74 is designed to be non-circular, which restricts the rotational freedom of the locking pin 73.

[0052] In the embodiment of the present application, the aircraft wing-body quick connection device further includes at least one compression spring 10. At least one compression spring 10 is arranged between the first docking seat 1 and the second docking seat 2 and is configured to limit the distance between the first docking seat 1 and the second docking seat 2 to ensure the stability and safety of the connection.

[0053] Specifically, two compression springs 10 are adopted in this embodiment. The two compression springs 10 are symmetrically arranged on both sides of the second stretching member 4 and are located inside the two guide rods 6. When the second stretching member 4 is pulled, the first docking seat 1 and the second docking seat 2 will overcome the resistance generated by the compression springs 10 and move towards each other. However, due to the elastic force of the compression springs 10, the moving distance of the first docking seat 1 and the second docking seat 2 will be limited and they will not move too much.

[0054] Further, when the wing body needs to be disassembled, the locking hook mechanism 3 will be activated again, simultaneously pulling the first stretching member 5 and the second stretching member 4. At this time, the locking mechanism 7 will withdraw from the limiting hole 81 and extend into the interiors of the first docking seat 1 and the second docking seat 2, thereby releasing their locked states. As the first docking seat 1 and the second docking seat 2 are completely removed from the limiting frame 8 of the fuselage 11, the second stretching member 4 will return to its initial state. Under the action of the compression spring 10, the first docking seat 1 and the second docking seat 2 will move away from each other until they return to their initial positions.

[0055] In the embodiment of the present application, the locking hook mechanism 3 includes a first lock housing 31, a second lock housing 32, a limiting seat 33, a latch hook 34, and a connecting rod 35. The first lock housing 31 is disposed on the skin of the fuselage 11. The second lock housing 32 is disposed on the skin of the wing surface 12 and corresponds to the first lock housing 31. The first lock housing 31 and the second lock housing 32 are located between the first docking seat 1 and the second docking seat 2. The limiting seat 33 is disposed on the first lock housing 31. A through hole is provided on the side of the second lock housing 32 away from the first lock housing 31, and one end of the connecting rod 35 passes through the through hole. The connecting rod 35 is provided with connecting holes at intervals along its height direction for the first stretching member 5 and the second stretching member 4 to pass through. One end of the latch hook 34 is rotatably connected to the side of the connecting rod 35 away from the connecting hole and is configured to pull the connecting rod 35 to move when the included angle with the second lock housing 32 is 90°. The other end of the latch hook 34 is a free end and is configured to be inserted into the limiting seat 33.

[0056] It should be noted that the operator first rotates the latch hook 34 until the included angle with the second lock housing 32 reaches 90°. Subsequently, the operator continues to pull the free end of the latch hook 34. During this process, the latch hook 34 will, through the transmission of the connecting rod 35, pull the connecting rod 35 and the first stretching member 5 and the second stretching member 4 connected thereto to move together. After the first docking seat 1 and the second docking seat 2 are respectively accurately inserted into the corresponding limiting frames 8 of the fuselage 11, the operator releases the latch hook 34. At this time, under the resilience of the first stretching member 5, the locking mechanism 7 will automatically return to its initial position, and the locking pin 73 will extend into the limiting hole 81 of the limiting frame 8 of the fuselage 11, thereby completing the locking action. Finally, the operator inserts the free end of the latch hook 34 into the limiting seat 33 to ensure that the locking hook mechanism 3 is in a stable locked state.

[0057] In the embodiment of the present application, the material of the latch hook 34 is hard rubber. The limiting seat 33 is a U-shaped structure 331, and the width of the top opening of the U-shaped structure 331 is smaller than the width of the bottom opening, such that after the latch hook 34 is pressed into the limiting seat 33, it can remain stable under any flight conditions and will not be disengaged due to vibration or external force. This self-locking mechanism enhances the reliability and safety of the latch hook 34.

[0058] In the embodiment of the present application, the locking hook mechanism 3 further includes a locking cover 36. The locking cover 36 is hinged to one end of the second lock housing 32 away from the first lock housing 31. A spring bolt 361 is provided on a side of the locking cover 36 away from the second lock housing 32. A socket 37 corresponding to the spring bolt 361 is provided on a side of the second lock housing 32 away from the first lock housing 31.

[0059] After the pull buckle locking hook 34 is pressed into the limit seat 33, the locking cover 36 is rotated to the first lock housing 31, and the spring bolt 361 is toggled to insert it into the socket 37, so as to fix the locking cover 36.

[0060] In the embodiment of the present application, the longitudinal sections of the first docking seat 1 and the second docking seat 2 are both of a first trapezoidal structure. The longitudinal section of the limit frame 8 of the fuselage 11 is a second trapezoidal structure corresponding to the first trapezoidal structure.

[0061] It should be noted that the second trapezoidal structure facilitates the insertion of the first docking seat 1 and the second docking seat 2.

[0062] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, reference can be made to each other. The key points of each embodiment are the differences from other embodiments.

[0063] The above embodiments are only used to illustrate the technical solutions of the present application, rather than limiting the present application; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. An aircraft wing-body quick connection device, characterized in that: It comprises a first docking seat (1), a second docking seat (2), a locking hook mechanism (3), a first stretching member (5), a second stretching member (4), at least one guide rod (6) and at least two locking mechanisms (7); Two ends of at least one of the guide rods (6) are respectively connected to adjacent beams (13) in the wing surface (12); The first docking seat (1) and the second docking seat (2) are respectively slidably connected to the two sides of the guide rod (6), and are located on the inner side of the adjacent beam (13) in the wing surface (12), and are configured to be inserted into the corresponding limit frame (8) of the fuselage (11); The first docking seat (1) and the second docking seat (2) are both provided with locking holes; One end of at least two of the locking mechanisms (7) passes through the corresponding locking holes and extends into the corresponding first docking seat (1) and the second docking seat (2); The limiting frame (8) of the fuselage (11) is provided with a limiting hole (81) corresponding to the locking hole; Two ends of the first stretching member (5) extend into the first docking seat (1) and the second docking seat (2) respectively, and are connected to the corresponding locking mechanism (7); Two ends of the second stretching member (4) are respectively connected to the first docking seat (1) and the second docking seat (2); The locking hook mechanism (3) is connected to the first stretching member (5) and the second stretching member (4), and is configured to pull the first stretching member (5) and the second stretching member (4), so that the first stretching member (5) drives the locking mechanism (7) located outside the locking hole to extend into the corresponding first docking seat (1) and the second docking seat (2), and at the same time, the second stretching member (4) drives the first docking seat (1) and the second docking seat (2) to move in a direction close to each other; Also includes at least one compression spring (10); At least one compression spring (10) is arranged between the first docking seat (1) and the second docking seat (2), and is configured to limit the distance between the first docking seat (1) and the second docking seat (2); The locking mechanism (7) comprises a guide column (74) and two locking pins (73); The two locking pins (73) are slidably connected to two sides of the guide column (74); One end portion of the two locking pins (73) away from the guide column (74) extends out of the corresponding locking hole; and the cross section of the guide column (74) is designed to be non-circular.

2. The aircraft wing-body quick connection device according to claim 1, characterized in that: The first tensioning member (5) comprises a rope (51), two resetting elastic members (52) and two baffles (53); The two resetting elastic members (52) and the two baffles (53) are respectively located in the first docking seat (1) and the second docking seat (2); Two ends of the rope (51) extend into the first docking seat (1) and the second docking seat (2) respectively, and pass through the corresponding baffle (53) to be connected to the corresponding locking mechanism (7); One end of each of the two resetting elastic members (52) is fixed to a side of the corresponding baffle (53) facing the locking mechanism (7), and the other end thereof abuts against the corresponding locking mechanism (7).

3. The aircraft wing-body quick connection device according to claim 2, characterized in that: It also includes two support guide seats (9); The two support guide seats (9) are respectively fixedly connected to the first docking seat (1) and the second docking seat (2), and are located on a side of the baffle (53) away from the locking mechanism (7); After the two ends of the rope (51) extend into the first docking seat (1) and the second docking seat (2), they bypass the corresponding support guide seat (9), and the support guide seat (9) is configured to guide the rope (51) to pass through the corresponding baffle (53).

4. The aircraft wing-body quick connection device according to claim 1, characterized in that: The locking mechanism (7) comprises a slider (71) and a tension spring (72); The first docking seat (1) and the second docking seat (2) are both provided with the sliding block (71) and the tension spring (72); Both ends of the first stretching member (5) are respectively connected to the corresponding sliding blocks (71); The slider (71) is a hollow structure; Two ends of the tension spring (72) respectively pass through the top wall and the bottom wall of the slider (71) and are connected to the two locking pins (73); two sides of the tension spring (72) abut against the top wall and the bottom wall of the slider (71); The longitudinal section of the sliding block (71) on the side away from the first stretching member (5) is a triangular structure; One end portion of the two locking pins (73) away from the tension spring (72) extends out of the corresponding locking hole, and the side of the two locking pins (73) close to the tension spring (72) is slidably connected to the top surface and bottom surface of the side of the slider (71) away from the first tension member (5).

5. The aircraft wing-body quick connection device according to claim 4, characterized in that: The tension spring (72) is sleeved on the outer wall of the guide column (74); The top surface and the bottom surface of the sliding block (71) on the side away from the first stretching member (5) are both provided with sliding grooves corresponding to the guide column (74).

6. The aircraft wing-body quick connection device according to claim 1, characterized in that: The lock hook mechanism (3) comprises a first lock housing (31), a second lock housing (32), a limit seat (33), a buckle lock hook (34) and a connecting rod (35); The first lock housing (31) is arranged on the skin of the fuselage (11); The second lock housing (32) is arranged on the skin of the wing surface (12) and corresponds to the first lock housing (31); The first lock housing (31) and the second lock housing (32) are located between the first docking seat (1) and the second docking seat (2); The limiting seat (33) is arranged on the first lock housing (31); A through hole is provided on a side of the second lock housing (32) away from the first lock housing (31), and one end of the connecting rod (35) passes through the through hole; The connecting rod (35) is provided with connection holes for the first tensile member (5) and the second tensile member (4) to pass through at intervals along its height direction; One end of the drawstring lock hook (34) is rotatably connected to a side of the connecting rod (35) away from the connecting hole, and is configured to pull the connecting rod (35) to move when the angle between the drawstring lock hook (34) and the second lock shell (32) is 90°; the other end of the drawstring lock hook (34) is a free end, and is configured to be inserted into the limit seat (33).

7. The aircraft wing-body quick connection device according to claim 6, characterized in that: The material of the buckle lock hook (34) is hard rubber; The limiting seat (33) is a U-shaped structure (331), and the width of the top opening of the U-shaped structure (331) is smaller than the width of the bottom opening thereof.

8. The aircraft wing-body quick connection device according to claim 6, characterized in that: The locking hook mechanism (3) further comprises a locking cover (36); The lock cover (36) is hinged to one end of the second lock housing (32) away from the first lock housing (31), and a spring latch (361) is provided on one side of the lock cover (36) away from the second lock housing (32); A pin seat (37) corresponding to the spring latch (361) is provided on a side of the second lock housing (32) away from the first lock housing (31).

9. The aircraft wing-body quick connection device according to claim 1, characterized in that: The longitudinal cross-sections of the first docking seat (1) and the second docking seat (2) are both first trapezoidal structures; The longitudinal section of the limiting frame (8) of the fuselage (11) is a second trapezoidal structure corresponding to the first trapezoidal structure.

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