Aircraft combination separation mechanism

Abstract

The utility model discloses an aircraft combination separation mechanism, including the right wing of aircraft no.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to an aircraft assembly and separation mechanism. Background Technology

[0002] Docking and separation technology for aircraft is one of the key technologies in the aerospace field. Current mainstream docking technologies include electromagnetic docking and mechanical locking. Existing technologies generally combine visual guidance with docking techniques, such as combining electromagnetic docking with visual guidance, to improve positioning accuracy. However, in practical applications, the lack of a mechanical locking mechanism and reliance solely on electromagnetic adsorption results in insufficient connection strength and stability. Alternatively, combining visual guidance with mechanical locking, while improving connection strength and docking stability, lacks the transition phase of electromagnetic adsorption, requiring higher initial docking accuracy and potentially leading to inaccurate docking. Therefore, we propose an aircraft assembly and separation mechanism. Utility Model Content

[0003] To address the aforementioned problems, this utility model provides an aircraft assembly and separation mechanism.

[0004] To achieve the above objectives, this utility model provides the following technical solution:

[0005] Design an aircraft assembly and separation mechanism, including the right wing of aircraft one and the left wing of aircraft two. The right wing end is connected to a right wing-end vertical wing, and the left wing end is connected to a left wing-end vertical wing. A magnetic positioning mechanism is provided between the right wing-end vertical wing and the left wing-end vertical wing. The magnetic positioning mechanism includes a positioning plate one and a positioning plate two that are magnetically attracted. A mechanical locking mechanism is provided between the right wing and the left wing. The mechanical locking mechanism includes a base that is detachably connected to the left wing. The base is provided with a quick-release locking pin that can move between the right wing-end vertical wing and the left wing-end vertical wing. A locking pin limiting sleeve that cooperates with the quick-release locking pin is installed in the right wing.

[0006] In the above scheme, the first positioning plate is connected to the right wing vertical wing, and the second positioning plate is connected to the left wing vertical wing.

[0007] In the above scheme, an electromagnetic chuck is installed on the first positioning plate, and a guide cylinder sleeved on the outside of the electromagnetic chuck is installed on the second positioning plate. A magnetic block that fits against the electromagnetic chuck is connected to the inner wall of the guide cylinder.

[0008] In the above scheme, the left wing surface is provided with a mounting groove for embedding the base, and the base is provided with a cover plate connected to the mounting groove.

[0009] In the above scheme, a linear motor with a drive end connected to a connecting rod is installed in the base, and push rods are installed at both ends of the connecting rod, with the quick-release locking pin connected to the end of the push rod.

[0010] In the above scheme, the push rod moves through the left wing and the left wing end vertical wing, and a buffer spring is sleeved at the end of the push rod.

[0011] In the above scheme, a cross screw slide module is provided below the right wing, a right wing lower clamping plate is installed at the bottom of the right wing, a left wing lower clamping plate is installed at the bottom of the left wing, and the right wing lower clamping plate is connected to the slider of the cross screw slide module through a pad.

[0012] The advantages and beneficial effects of this utility model are as follows: By setting up a right-wing vertical wing, a left-wing vertical wing, a magnetic positioning mechanism, and a mechanical locking mechanism, the right-wing and left-wing vertical wings serve as the mounting planes for the magnetic positioning mechanism. Combined with positioning plates one and two, the two are magnetically attracted, causing the right-wing and left-wing vertical wings to adhere and fix each other, thus allowing aircraft one and aircraft two to be assembled. The quick-release locking pin and locking pin limit sleeve further lock the two together. Compared to existing technologies, on the one hand, the magnetic positioning mechanism allows for precise positioning and docking of aircraft one and aircraft two, effectively improving docking accuracy. On the other hand, the mechanical locking mechanism enhances the docking load-bearing capacity of aircraft one and aircraft two, effectively improving connection strength and stability, and increasing the reliability of the docking action. Furthermore, by changing the shape, size, and material of the right-wing and left-wing vertical wings, the magnetic positioning mechanism, and the mechanical locking mechanism, it can be adapted to different models of aircraft one and aircraft two, expanding its application range. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0014] Figure 1 This is a front view of an aircraft assembly and separation mechanism proposed in this utility model;

[0015] Figure 2 This is a top view of an aircraft assembly and separation mechanism proposed in this utility model;

[0016] Figure 3 This is a top sectional view of the right and left wings of an aircraft assembly and separation mechanism proposed in this utility model;

[0017] Figure 4 This is a right view of an aircraft assembly and separation mechanism proposed in this utility model;

[0018] Figure 5 This is a cross-sectional view of a magnetic positioning mechanism for an aircraft assembly separation mechanism proposed in this utility model.

[0019] In the diagram: Right wing 1, Left wing 2, Quick release locking pin 3, Right wing end vertical wing 4, Left wing end vertical wing 5, Connecting rod 6, Locking pin limit sleeve 7, Magnetic positioning mechanism 8, Cover plate 9, Linear motor 10, Right wing lower clamping plate 11, Pad block 12, Left wing lower clamping plate 13, Buffer spring 14, Push rod 15, Cross screw slide module 16, Mounting groove 17, Base 18, Positioning plate one 19, Positioning plate two 20, Electromagnetic chuck 21, Guide cylinder 22, Magnetic block 23. Detailed Implementation

[0020] The specific embodiments of this utility model will be further described below with reference to the accompanying drawings and examples. The following examples are only used to more clearly illustrate the technical solution of this utility model and should not be construed as limiting the scope of protection of this utility model.

[0021] Please see Figure 1-5 This utility model provides a technical solution: an aircraft assembly and separation mechanism, comprising the right wing 1 of an aircraft one and the left wing 2 of an aircraft two. Figure 1 The left side is the right wing 1 of aircraft one, and the right side is the left wing 2 of aircraft two. When the right wing 1 and the left wing 2 dock, that is, aircraft one and aircraft two complete the docking. The end of the right wing 1 is connected to the longitudinally arranged right wing vertical wing 4 by countersunk screws. The end of the left wing 2 is connected to the longitudinally arranged left wing vertical wing 5 by countersunk screws. A magnetic positioning mechanism 8 is provided between the right wing vertical wing 4 and the left wing vertical wing 5. The magnetic positioning mechanism 8 includes a magnetically adsorbed positioning plate 19 and a positioning plate 20.

[0022] Furthermore, positioning plate 19 is connected to the right wing vertical wing 4 by countersunk screws, and positioning plate 20 is connected to the left wing vertical wing 5 by countersunk screws.

[0023] Furthermore, an electromagnetic chuck 21 is installed on the positioning plate 19, and a guide cylinder 22 sleeved on the outside of the electromagnetic chuck 21 is installed on the positioning plate 20. A magnetic block 23 that fits against the electromagnetic chuck 21 is connected to the inner wall of the guide cylinder 22. The side of the magnetic block 23 closest to the electromagnetic chuck 21 has opposite magnetic poles to the electromagnetic chuck 21. The magnetic force is used to attract and fix the magnetic block 23 and the electromagnetic chuck 21. The guide cylinder 22 is used to guide the electromagnetic chuck 21 and the guide cylinder 22 to connect, which helps to improve the docking accuracy.

[0024] A mechanical locking mechanism is provided between the right wing 1 and the left wing 2. The mechanical locking mechanism includes a base 18 that is detachably connected to the left wing 2.

[0025] Specifically, such as Figure 4 As shown, the positioning plate 20 is located on the upper surface of the left wing vertical wing 5 away from the left wing 2, while the quick-release locking pin 3 mentioned below is located on the lower surface of the left wing vertical wing 5 away from the left wing 2.

[0026] Furthermore, the surface of the left wing 2 is provided with a mounting groove 17 for embedding the base 18. The base 18 is provided with a cover plate 9 connected to the mounting groove 17 by countersunk screws, which facilitates the disassembly and assembly of the base 18 and the cover plate 9, so as to replace the base 18 and related structures inside the base 18, making it more modular. The cover plate 9 provides dust protection for the base 18 and related structures inside the base 18.

[0027] The base 18 is provided with a quick-release locking pin 3 that can move between the right wing vertical 4 and the left wing vertical 5. The right wing 1 is equipped with a locking pin limiting sleeve 7 that cooperates with the quick-release locking pin 3. The right wing 1 is connected to the locking pin limiting sleeve 7 by a countersunk screw, so that the locking pin limiting sleeve 7 is easy to disassemble and assemble.

[0028] Furthermore, a linear motor 10 with a connecting rod 6 connected to the drive end is installed inside the base 18. The linear motor 10 is connected to the inner wall of the base 18 through a bracket. Push rods 15 are installed at both ends of the connecting rod 6. The push rods 15 are connected to the ends of the connecting rod 6 through countersunk screws. The quick-release locking pin 3 is connected to the end of the push rod 15.

[0029] Furthermore, the push rod 15 moves through the left wing 2 and the left end vertical wing 5. The left wing 2 and the left end vertical wing 5 are provided with moving grooves for the push rod 15 to move left and right, and the end of the push rod 15 (a section away from the connecting rod 6) is fitted with a buffer spring 14.

[0030] Specifically, the quick-release locking pin 3 includes a limiting plate, a sleeve, and a ball pin. The ball pin is slidably connected inside the sleeve. The end of the push rod 15 is coaxially connected to the ball pin. The diameter of the limiting plate is larger than the outer diameter of the sleeve. The left wing end vertical wing 5 is provided with a sliding groove that allows the annular limiting plate to move left and right. The sliding groove does not penetrate through both sides of the left wing end vertical wing 5. The sliding groove is connected to the moving groove. The diameter of the push rod 15 is much smaller than the diameter of the limiting plate. The sleeve is fixed to the left wing end vertical wing 5. The limiting plate is coaxially fixed to the ball pin. One end of the buffer spring 14 is connected to the right side of the limiting plate, and the other end of the buffer spring 14 is connected to the inner wall of the right side of the sliding groove.

[0031] Specifically, by setting up a right-wing vertical wing 4, a left-wing vertical wing 5, a magnetic positioning mechanism, and a mechanical locking mechanism, the right-wing vertical wing 4 and the left-wing vertical wing 5 serve as the mounting plane for the magnetic positioning mechanism. Together with positioning plate 19 and positioning plate 20, they magnetically attract each other, thus fixing the right-wing vertical wing 4 and the left-wing vertical wing 5 together, thereby completing the assembly of aircraft one and aircraft two. Combined with quick-release locking pin 3 and locking pin limiting sleeve 7, the two are locked together, thus locking aircraft one and aircraft two together. Compared to existing... On the one hand, the magnetic positioning mechanism is used to precisely position and dock aircraft one and aircraft two, effectively improving docking accuracy. On the other hand, the mechanical locking mechanism enhances the docking load-bearing capacity of aircraft one and aircraft two, effectively improving connection strength and stability, and improving the reliability of docking operations. In addition, by changing the shape, size and material of the right wing vertical 4, the left wing vertical 5, the magnetic positioning mechanism and the mechanical locking mechanism, it can be adapted to different models of aircraft one and aircraft two, thus expanding the application range.

[0032] Furthermore, a cross screw slide module 16 is provided below the right wing 1, and a right wing lower clamping plate 11 is installed at the bottom of the right wing 1 by countersunk screws. A left wing lower clamping plate 13 is installed at the bottom of the left wing 2 by countersunk screws. The right wing lower clamping plate 11 is connected to the slider of the cross screw slide module 16 by a pad 12. The pad 12 is connected to the slider and the right wing lower clamping plate 11 by countersunk screws.

[0033] Working principle:

[0034] 1. The initial attitude of the second aircraft is adjusted by a visual camera. After reaching a certain distance range, the electromagnetic chuck 21 is used to capture its approach. The electromagnetic chuck 21 and the magnetic block 23 in the guide cylinder 22 attract each other for guidance and positioning. The quick-release locking pin 3 of the second aircraft is inserted into the locking pin limiting sleeve 7 of the first aircraft. Then, the linear motor 10 drives the quick-release locking pin 3 to lock it with the locking pin limiting sleeve 7. The first aircraft and the second aircraft achieve a rigid connection, and the entire docking process is completed.

[0035] 2. The control system of aircraft one controls the electromagnetic chuck 21 to release the magnetic force, and aircraft two drives the quick release locking pin 3 through the drive linear motor 10 to unlock it from the locking pin limit sleeve 7, thus completing the entire separation process.

[0036] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. An aircraft assembly and separation mechanism, comprising a right wing (1) of an aircraft one and a left wing (2) of an aircraft two, characterized in that, The right wing (1) is connected to a right wing vertical wing (4) at its end, and the left wing (2) is connected to a left wing vertical wing (5) at its end. A magnetic positioning mechanism (8) is provided between the right wing vertical wing (4) and the left wing vertical wing (5). The magnetic positioning mechanism (8) includes a magnetically adsorbed positioning plate one (19) and a positioning plate two (20). A mechanical locking mechanism is provided between the right wing (1) and the left wing (2). The mechanical locking mechanism includes a base (18) detachably connected to the left wing (2). A quick-release locking pin (3) that can move between the right wing vertical wing (4) and the left wing vertical wing (5) is provided in the base (18). A locking pin limiting sleeve (7) that cooperates with the quick-release locking pin (3) is installed in the right wing (1).

2. A combined separation mechanism for an aircraft according to claim 1, characterised in that The first positioning plate (19) is connected to the right wing vertical wing (4), and the second positioning plate (20) is connected to the left wing vertical wing (5).

3. A combined separation mechanism for an aircraft according to claim 2, wherein, An electromagnetic chuck (21) is installed on the first positioning plate (19), and a guide cylinder (22) sleeved on the outside of the electromagnetic chuck (21) is installed on the second positioning plate (20). A magnetic block (23) that fits against the electromagnetic chuck (21) is connected to the inner wall of the guide cylinder (22).

4. The aircraft combined separation mechanism of claim 1, wherein, The left wing (2) has a mounting groove (17) for embedding the base (18) on its surface, and the base (18) has a cover plate (9) connected to the mounting groove (17).

5. The aircraft combined separation mechanism of claim 1, wherein, The base (18) is equipped with a linear motor (10) with a connecting rod (6) at the drive end. Both ends of the connecting rod (6) are equipped with push rods (15), and the quick-release locking pin (3) is connected to the end of the push rod (15).

6. The aircraft assembly and separation mechanism according to claim 5, characterized in that, The push rod (15) moves through the left wing (2) and the left wing end vertical wing (5), and a buffer spring (14) is sleeved at the end of the push rod (15).

7. The aircraft combined separation mechanism of claim 1, wherein, The right wing (1) is provided with a cross screw slide module (16) below it, and a right wing lower clamping plate (11) is installed at the bottom of the right wing (1). The left wing (2) is provided with a left wing lower clamping plate (13) at the bottom. The right wing lower clamping plate (11) is connected to the slider of the cross screw slide module (16) through a pad (12).

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