Wing-fuselage assembly structure and aircraft having the same

Abstract

The present invention discloses a wing-fuselage assembly structure, comprising a locking pin, a locking piece and an unlocking mechanism, wherein the locking pin is arranged on the wing and / or the fuselage, and the locking piece is arranged on the fuselage and / or the wing, and when the locking pin is locked with the locking piece, the wing and the fuselage are relatively fixed; the locking pin is provided with a recessed structure located at the rear side of its head; the locking piece comprises a locking tongue and an elastic piece, and when the locking pin moves toward the direction of its head, its head presses the locking tongue, so that the locking tongue moves toward the direction of the tail of the locking tongue, and the elastic piece is elastically deformed, and when the recessed structure passes through the locking tongue, the elastic piece restores the elastic deformation force to lock the locking tongue on the recessed structure; the unlocking structure is connected with the locking tongue, and can drive the locking tongue to leave the recessed structure under the action of an external force.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft connection structures, and in particular to a wing-fuselage assembly structure and an aircraft having the wing-fuselage assembly structure. Background Art

[0002] In the prior art, drones, aircraft, and model airplanes usually have wings and fuselages that are detachable in order to save space. When assembling the wings and fuselage, screws are usually used to connect and fix them, and the operation process is relatively cumbersome. With the rapid development of drone technology, drones have gradually begun to assume the function of logistics transportation. For example, when transporting goods through the fuselage of a drone, only the fuselage needs to be operated during loading and unloading, while the wings are idle. If the wings can be quickly disassembled and assembled, the idle wings can be used for other drones that are about to take off. Therefore, the speed of disassembly and assembly of the wings can easily affect the allocation of resources and the work efficiency of the drone, and the connection method between the wings and the fuselage in the prior art cannot meet the needs of the industry.

[0003] Currently, no effective solution has been proposed for the problems in the related technologies. Summary of the invention

[0004] In view of the above technical problems in the related art, the present invention proposes a wing-fuselage assembly structure, which can realize the rapid disassembly and assembly of the wing and the fuselage, and has the advantages of simple structure, convenient operation, low cost, reliable connection, etc. Another aspect of the present invention also provides an aircraft, which can realize the rapid disassembly and assembly of the wing and the fuselage, and has a sufficiently high connection strength.

[0005] To achieve the above technical objectives, the technical solution of the present invention is implemented as follows:

[0006] A wing-fuselage assembly structure, comprising a locking pin, a locking member and an unlocking mechanism, wherein the locking pin is arranged on the wing and / or the fuselage, the locking member is arranged on the fuselage and / or the wing, and when the locking pin is locked to the locking member, the wing and the fuselage are relatively fixed;

[0007] The locking pin is provided with a recessed structure located at the rear side of its head;

[0008] The locking member includes a locking tongue and an elastic member. When the locking pin moves toward the head direction, the head of the locking pin presses the locking tongue, so that the locking tongue moves toward the tail of the locking tongue and the elastic member generates elastic deformation. When the recessed structure passes through the locking tongue, the elastic member restores the elastic deformation force so that the locking tongue is locked on the recessed structure.

[0009] The unlocking mechanism is connected to the locking tongue and can drive the locking tongue to leave the recessed structure under the action of an external force.

[0010] Preferably, the unlocking mechanism comprises an operating rod connected to the tail of the locking tongue.

[0011] Preferably, the operating rod comprises an operating portion and a connecting portion, the operating portion is a regular hexagonal column, and the connecting portion is fixedly connected to the tail of the locking tongue.

[0012] Preferably, one end of the operating rod extends to the outside of the wing or fuselage.

[0013] Preferably, the locking member includes a shell, the shell includes a slide groove, the lock tongue can slide along the slide groove, and a limiting portion is provided at the tail of the lock tongue, and the limiting portion can be stuck on the outside of the slide groove so that the lock tongue cannot escape from the slide groove.

[0014] Preferably, the elastic member comprises a spring, and the spring is sleeved on the locking tongue.

[0015] Preferably, the outer shell includes an unlocking retaining groove connected to the slide groove, and the operating rod is provided with an unlocking retaining structure. When the wing-fuselage assembly structure is in an unlocked state, the unlocking retaining structure can be rotated to be stuck in the unlocking retaining groove.

[0016] Preferably, the unlocking and retaining groove is a circular groove-shaped structure, and the sliding groove is a rectangular groove-shaped structure.

[0017] Another aspect of the present invention provides an aircraft, comprising a separate fuselage and wings, and also comprising the above-mentioned wing-fuselage assembly structure or an improved structure thereof.

[0018] Preferably, the fuselage is provided with a main beam square rod, and the wing is provided with a main beam docking interface corresponding to the main beam square rod.

[0019] Preferably, connectors are provided on the wings and / or fuselage.

[0020] Preferably, a locating pin is provided on the wing, and a locating pin hole corresponding to the locating pin is provided on the fuselage.

[0021] Beneficial effects of the present invention: The wing-fuselage assembly structure and the aircraft having the same described in the present invention can realize the assembly of the wing and the fuselage by providing a locking pin and a locking member, and can realize automatic locking between the locking pin and the locking member during installation by providing an elastic member, thereby improving the assembly efficiency of the wing and the fuselage, and can quickly realize the disassembly of the wing and the fuselage by providing an unlocking mechanism, thereby improving the disassembly efficiency of the wing and the fuselage.

[0022] The wing-fuselage assembly structure and the aircraft having the same described in the present invention have the advantages of simple structure, low cost, convenient operation, reliable connection, etc., and are suitable for popularization and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 is a top view of the wing-fuselage assembly structure in a locked state according to an embodiment of the present invention;

[0025] Figure 2 is a three-dimensional diagram of the wing-fuselage assembly structure in a locked state according to an embodiment of the present invention;

[0026] Figure 3 is a three-dimensional exploded view of the wing-fuselage assembly structure in a locked state according to an embodiment of the present invention;

[0027] Figure 4 is a top view of the wing-fuselage assembly structure in an unlocked state according to an embodiment of the present invention;

[0028] Figure 5 is a three-dimensional diagram of the wing-fuselage assembly structure in an unlocked state according to an embodiment of the present invention;

[0029] Figure 6 is a three-dimensional diagram of the unlocking and holding structure according to an embodiment of the present invention;

[0030] Figure 7 is a three-dimensional diagram of a housing according to an embodiment of the present invention;

[0031] Figure 8 is a three-dimensional diagram of the aircraft according to an embodiment of the present invention in an assembled state;

[0032] Fig. 9 is a three-dimensional diagram of the aircraft according to an embodiment of the present invention in a disassembled state;

[0033] Fig.10 is a three-dimensional diagram showing a partial fuselage structure of the aircraft according to an embodiment of the present invention in an assembled state;

[0034] Fig.11 yes Fig.10 Enlarged view of the middle circled portion A;

[0035] Fig.12 yes Fig.10Enlarged view of the middle circle B;

[0036] Fig.13 It is a stereoscopic diagram of the unlocking and holding structure and the operating lever in the embodiment of the present invention in a combined state.

[0037] In the figure: 1. Wing-fuselage assembly structure; 2. Wing; 3. Fuselage;

[0038] 10. Locking pin; 20. Locking member; 30. Unlocking mechanism; 40. Unlocking holding structure;

[0039] 11. Depression structure;

[0040] 21. Lock tongue; 22. Elastic member; 23. Housing; 24. Stopper; 25. Boss;

[0041] 31. Operating lever; 311. Operating part; 312. Connecting part;

[0042] 41. Step portion; 42. Sliding surface; 43. Threaded hole;

[0043] 211. Limiting part; 212. Head of the lock tongue; 221. Spring; 231. Slide groove; 232. Unlocking holding groove; 251. Slide rail;

[0044] 201. Main beam docking port; 202. Connector; 203. Positioning pin; 301. Main beam square rod; 302. Locking pin hole;

[0045] 2111.Connection hole. DETAILED DESCRIPTION

[0046] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the present invention.

[0047] like Figures 1 to 5 As shown, a wing-fuselage assembly structure according to an embodiment of the present invention is shown.

[0048] like Figure 1 As shown, the wing-fuselage assembly structure 1 includes a locking pin 10 , a locking member 20 and an unlocking mechanism 30 .

[0049] When the wing-fuselage assembly structure 1 is applied to the wing 2 and the fuselage 3, the locking pin 10 is arranged on the wing 2 and / or the fuselage 3, and the locking member 20 is arranged on the fuselage 3 and / or the wing 2. Fig. 9 , 11As shown, the locking pin 10 is arranged on the wing 2, the locking member 20 is arranged on the fuselage 3, and a locking pin hole 302 matching with the locking pin 10 is provided on the fuselage 3. Of course, other situations are also possible, for example, the locking pin 10 is arranged on the fuselage 3, and the locking member 20 is arranged on the wing 2. For another example, two sets of wing-fuselage assembly structures 1 are provided, a locking pin 10 and a locking member 20 are provided on the wing 2 at the same time, and a locking member 20 and a locking pin 10 are provided on the fuselage accordingly. Even more than two sets of wing-fuselage assembly structures 1 can be provided as required.

[0050] like Figure 2 , Figure 4 As shown, the locking pin 10 is provided with a recessed structure 11 located at the rear side of its head; the locking member 20 includes a locking tongue 21 and an elastic member 22. When the locking pin 10 moves toward its head, its head presses the locking tongue 21, causing the locking tongue 21 to move toward the tail of the locking tongue 21 (i.e., the unlocking direction), and causing the elastic member 22 to produce elastic deformation. When the locking pin 10 continues to move until the recessed structure 11 passes the locking tongue 21, the elastic member 22 restores the elastic deformation force to cause the locking tongue 21 to move toward the head of the locking tongue 21 (i.e., the locking direction), and be fixed inside the recessed structure 11, i.e., be locked on the recessed structure 11.

[0051] The elastic member 22 can be, for example, a spring 221 sleeved on the locking tongue 21, or an elastic rubber arranged at the tail of the locking tongue 21. By appropriately arranging a structure to limit the movement of the elastic member 22 around the elastic member 22, the elastic member 22 can be squeezed and elastically deformed once the locking tongue 21 moves toward its tail. When the recessed structure 11 passes through the locking tongue 21, the squeezing force disappears, and the force of the elastic member 22 to restore the deformation can push the locking tongue 21 into the recessed structure 11 to complete the locking. At this time, the wing 2 and the fuselage 3 are relatively fixed.

[0052] Figure 5 The wing-fuselage assembly structure 1 is shown in an unlocked state, that is, a state where the recessed structure 11 of the locking pin 10 has not passed through the locking tongue 21 . Figure 2 The figure shows the locked state of the wing-fuselage assembly structure 1 , that is, the recessed structure 11 of the locking pin 10 passes through the locking tongue 21 , and the head of the locking tongue 21 enters the recessed structure 11 .

[0053] The head of the locking pin 10 may be a hemispherical structure, which has an arc that can smoothly push the head of the locking tongue 21, so that the locking tongue 21 moves toward the tail of the locking tongue 21 (i.e., the unlocking direction). The locking process of the wing-fuselage assembly structure 1 is as follows: the recessed structure 11 is arranged toward the locking tongue 21, and when the locking pin 10 moves toward the locking member 20 (in Figure 1 As a reference, i.e. to the left), the head of the locking pin 10 pushes the locking tongue 21 in the unlocking direction (with Figure 1As a reference, that is, downward) until the recessed structure 11 is aligned with the lock tongue 21, at which time, the elastic member 22 restores the deformation force to push the lock tongue 21 in the locking direction (with Figure 1 For reference, the lock tongue 21 moves upward, the head of the lock tongue 21 is stuck on the recessed structure 11, and the locking is completed. The state of the locking is as shown in FIG. Figure 1 and Figure 2 shown.

[0054] Since the lock tongue is usually located inside the wing 2 or the fuselage 3, it is difficult and inefficient to directly drive the lock tongue 21 to unlock and separate the wing 2 and the fuselage 3. Figure 1 As shown, the locking member 20 further includes an unlocking mechanism 30 , which is connected to the locking tongue 21 . The unlocking mechanism 30 can drive the locking tongue 21 to leave the recessed structure 11 under the action of an external force.

[0055] The unlocking process of the wing-fuselage assembly structure 1 is as follows: the unlocking mechanism 30 is applied in the unlocking direction (with Figure 1 The unlocking mechanism 30 transmits the force to the lock tongue 21, so that the lock tongue 21 moves in the unlocking direction until the head of the lock tongue 21 is completely separated from the recessed structure 11. At this time, the locking pin 10 and the locking member 20 can be separated to complete the unlocking. The unlocking state is as shown in FIG. Figure 4 and Figure 5 shown.

[0056] A specific implementation of the unlocking mechanism 30 is as follows: Figure 2 , Figure 5 As shown, the unlocking mechanism 30 includes an operating rod 31, and the operating rod 31 is connected to the tail of the lock tongue 21. The operating rod 31 is perpendicular to the lock tongue 21, and a force is applied to the operating rod 31, thereby pulling the lock tongue 21 to move in the unlocking direction to achieve unlocking.

[0057] As a further improvement of the unlocking mechanism 30, the operating rod 31 extends to the outside of the wing 2 or the fuselage 3. At this time, the unlocking mechanism 30 can be operated to unlock from the outside of the aircraft, which is convenient and quick.

[0058] As a further improvement of the embodiment of the present invention, Figure 2 and Figure 5 As shown, the locking member 20 includes a housing 23 for integrating the locking tongue 21 and the elastic member 22. The housing 23 is provided with a locking tongue hole (the locking tongue hole is not shown) for the locking tongue 21 to pass through. Figure 3As shown, the housing 23 includes a slide groove 231, which is a generally rectangular groove-shaped structure. The lock tongue 21 can slide along the inner side of the slide groove 231. A limiting portion 211 is provided at the rear of the lock tongue 21. The limiting portion 211 can be stuck on the outer side of the slide groove 231 so that the lock tongue 21 cannot escape from the slide groove 231. Specifically, the width of the limiting portion 211 is greater than the inner width of the slide groove 231. In this way, the limiting portion 211 can be stuck on the outer side of the slide groove 231, so that the lock tongue 21 cannot continue to move in the locking direction (with Figure 1 for reference, i.e. upwardly) to prevent the locking tongue 21 from falling out of the sliding groove 231.

[0059] A specific implementation of the locking member 20 is as follows: Figure 3 As shown, the elastic member 22 is a spring 221, and the spring 221 is sleeved on the lock tongue 21. Figure 3 and Figure 4 As shown, a block 24 is provided on each side of the tail of the slide slot 231, the width of the head 212 of the lock tongue 21 is greater than the width of the spring 221, and the spring 221 is restricted between the block 24 and the head 212 of the lock tongue 21. When the lock tongue 21 moves in the unlocking direction, the distance between the block 24 and the head 212 of the lock tongue 21 becomes shorter, the spring 221 is compressed, and elastic deformation occurs, and the spring 221 applies force to the head 212 of the lock tongue 21, so that the lock tongue 21 has a tendency to move in the locking direction.

[0060] As a further improvement of the embodiment of the present invention, Figure 3 As shown, the housing 23 includes an unlocking holding groove 232 connected to the slide groove 231, and an unlocking holding structure 40 is provided on the operating rod 31. When the wing-fuselage assembly structure 1 is in the unlocking state, the unlocking holding structure 40 can be rotated to be stuck in the unlocking holding groove 232. Accordingly, the unlocking state can be kept when needed (for example, during maintenance and repair, or during disassembly), so that the lock tongue 21 will not be pushed to the locking position by the elastic member 22.

[0061] A specific implementation of the unlocking holding structure 40 is as follows: Figure 6 As shown, it is roughly in the shape of a cuboid, with its short side smaller than the width of the inner side of the slide slot 231, and its long side larger than the width of the inner side of the slide slot 231. In the locked state, the short side of the unlocking holding structure 40 can extend into the slide slot 231, and in the unlocked state, the unlocking holding structure 40 is rotated so that the long side faces the slide slot 231. Since the long side is larger than the width of the inner side of the slide slot 231, the unlocking holding structure 40 in the locked state can be stuck outside the slide slot 231, as shown in FIG. Figure 4 and Figure 5 The unlocking and holding structure 40 is further rotated to make the short side face the slide groove 231. Since the short side is smaller than the inner side of the slide groove 231, the unlocking and holding structure 40 moves in the locking direction along with the lock tongue 21 under the action of the elastic member 22. Figure 1 and Figure 2 As shown, release the unlock hold state.

[0062] The bottom surface of the unlocking and holding structure 40 is provided with a step portion 41 protruding downward, so that the edge of the bottom of the unlocking and holding structure 40 forms a square sliding surface 42, and the center of the unlocking and holding structure 40 is provided with a threaded hole 43 for connecting with the operating rod 31. Figure 7 As shown, the unlocking and holding groove 232 is generally a circular groove structure, and its diameter is larger than the width of the inner side of the slide groove 231, and is connected to the slide groove 231. The inner side walls of the unlocking and holding groove 232 and the slide groove 231 are provided with a boss 25 protruding inward, and the top of the boss 25 forms a slide rail 251, and the slide surface 42 is stuck on the slide rail 251. When the unlocking and holding structure 40 rotates, the slide surface 42 slides along the slide rail 251.

[0063] The shape of the unlocking and holding structure 40 is not limited to the above-mentioned specific forms, as long as the unlocking and holding structure 40 can enter the slide groove 231 when it is rotated to certain positions and cannot enter the slide groove 231 when it is rotated to other positions. The shape and structure of the unlocking and holding groove 232 is also not limited to the above-mentioned specific forms, as long as the unlocking and holding structure 40 can be stuck or clamped when it is rotated to certain positions.

[0064] As a further improvement of the embodiment of the present invention, Fig.13 As shown, the operating rod 31 includes an operating portion 311 and a connecting portion 312. The operating portion 311 is a regular hexagonal column, so that the operator can judge the approximate rotation position of the unlocking and holding structure 40 according to the rotation of the operating portion 311 without being able to see the specific structure of the wing-fuselage assembly structure 1. The connecting portion 312 is used to connect with the tail of the locking tongue 21, such as Figure 3 As shown, a connection hole 2111 is provided on the limiting portion 211 disposed on the rear portion of the locking tongue 21 , and the connection portion 312 extends into the connection hole 2111 , so that the operating rod 31 is fixedly connected to the locking tongue 21 .

[0065] Next, the aircraft according to the present invention will be described.

[0066] like Figures 8 to 10 As shown, the aircraft includes a wing 2 and a fuselage 3. In addition, it also includes the above-mentioned wing-fuselage assembly structure 1 or its improved structure. Since how the wing-fuselage assembly structure 1 is applied to the wing 2 and fuselage 3 of the aircraft has been described in detail, it will not be repeated here.

[0067] like Figures 1 to 5 8 to 12, when the wing 2 is docked with the fuselage 3, the locking pin 10 and the locking member 20 of the wing-fuselage assembly structure 1 are automatically locked, completing the installation of the wing 2 and the fuselage 3, and the state is as shown in FIG. Figure 8 and Fig.10When disassembling the wing 2, pull the operating rod 31 to make the unlocking and holding structure 40 enter the unlocking and holding groove 232, and then pull out the wing 2 to complete the disassembly. Fig. 9 The operating rod 31 is rotated to rotate the unlocking and holding structure 40 by 180° to enter the unlocking and holding state, and maintenance and repair work can be carried out.

[0068] As a further improvement to the aircraft, Fig. 9 As shown, the fuselage 3 is provided with a main beam square rod 301, and the wing 2 is provided with a main beam docking port 201 corresponding to the main beam square rod 301. The main beam square rod 301 is connected to the main beam of the fuselage, and serves as the main load-bearing rod of the aircraft to bear the shear flow. The wing-fuselage assembly structure 1 constitutes a main limit module and a quick-release functional module. When the wing 2 is docked with the fuselage 3, the main beam square rod 301 docks with the main beam docking port 201 to achieve guided sliding.

[0069] As a further improvement to the aircraft, a connector 202 is provided on the wing 2 and / or the fuselage 3. The connector 202 is used to facilitate electrical connection or signal connection between various components of the aircraft. Fig. 9 As shown, the connector 202 can be arranged on the wing 2; Fig.12 As shown, the connector 202 may also be disposed on the fuselage 3; Fig. 9 As shown, the connector 202 can also be arranged on the wing 2 and the fuselage 3 at the same time.

[0070] As a further improvement to the aircraft, Fig. 9 As shown, the wing 2 is provided with a locating pin 203, and the fuselage 3 is provided with a locating pin hole corresponding to the locating pin 203. The locating pin 203 serves as an auxiliary locating point between the wing 2 and the fuselage 3, and is used to increase the connection strength.

[0071] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A wing-fuselage assembly structure, characterized in that: It comprises a locking pin, a locking member and an unlocking mechanism, wherein the locking pin is arranged on the wing and / or the fuselage, the locking member is arranged on the fuselage and / or the wing, and when the locking pin is locked to the locking member, the wing and the fuselage are relatively fixed; The locking pin is provided with a recessed structure located at the rear side of its head; The locking member includes a locking tongue and an elastic member. When the locking pin moves toward the head direction, the head of the locking pin presses the locking tongue, so that the locking tongue moves toward the tail of the locking tongue and the elastic member generates elastic deformation. When the recessed structure passes through the locking tongue, the elastic member restores the elastic deformation force so that the locking tongue is locked on the recessed structure. The unlocking mechanism is connected to the lock tongue, and can drive the lock tongue to leave the recessed structure under the action of external force; The unlocking mechanism includes an operating rod connected to the tail of the locking tongue; The operating rod comprises an operating portion and a connecting portion, wherein the operating portion is a regular hexagonal column, and the connecting portion is fixedly connected to the tail of the locking tongue.

2. The wing-fuselage assembly structure according to claim 1, characterized in that: One end of the operating rod extends to the outside of the wing or fuselage.

3. The wing-fuselage assembly structure according to claim 1, characterized in that: The locking member comprises a shell, the shell comprises a slide groove, the locking tongue can slide along the slide groove, and a limiting portion is provided at the tail of the locking tongue, and the limiting portion can be stuck on the outside of the slide groove so that the locking tongue cannot escape from the slide groove.

4. The wing-fuselage assembly structure according to claim 1, characterized in that: The elastic member comprises a spring, and the spring is sleeved on the locking tongue.

5. The wing-fuselage assembly structure according to claim 3, characterized in that: The shell includes an unlocking and holding groove connected to the slide groove, and the operating rod is provided with an unlocking and holding structure. When the wing-fuselage assembly structure is in an unlocked state, the unlocking and holding structure can be rotated to be stuck in the unlocking and holding groove.

6. The wing-fuselage assembly structure according to claim 5, characterized in that: The unlocking and holding groove is a circular groove structure, and the sliding groove is a rectangular groove structure.

7. An aircraft comprising a separate fuselage and wings, characterized in that: It comprises the wing-fuselage assembly structure as described in any one of claims 1 to 6.

8. The aircraft according to claim 7, characterized in that A main beam square rod is arranged on the fuselage, and a main beam docking interface corresponding to the main beam square rod is arranged on the wing.

9. The aircraft according to claim 7, characterized in that: The wings and / or the fuselage are provided with connectors.

10. The aircraft according to claim 7, characterized in that: The wing is provided with a positioning pin, and the fuselage is provided with a positioning pin hole corresponding to the positioning pin.

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