A spacecraft landing gear forming device

Abstract

The utility model relates to space vehicle landing gear forming technical field discloses a space vehicle landing gear forming device, including the hot press jar, the lower extreme outer surface fixed connection of hot press jar has the base, the front end outer surface detachable connection of hot press jar has the jar door, the inner wall swing joint of hot press jar has the blank placing table, the inner wall fixed connection of hot press jar has the slide rail, blank placing table and the slide rail between are the sliding connection, the lower extreme outer surface of blank placing table is provided with support assembly, support assembly includes the connecting plate, recess no.

Description

Technical Field

[0001] This utility model relates to the field of spacecraft landing gear forming technology, specifically a spacecraft landing gear forming device. Background Technology

[0002] The forming principle of spacecraft landing gear mainly includes autoclave curing and non-autoclave forming technologies. In the civil aviation field, in autoclave-cured composite material structures, the cost of the matrix material accounts for only about 15%, while the manufacturing cost (such as layup, assembly, machining, etc.) is as high as 70% to 80%. Labor cost is a key factor affecting the cost of composite material parts. Autoclave forming refers to the process of placing a composite material blank made of single-layer prepreg laid in a predetermined direction in an autoclave and completing the curing process under a certain temperature and pressure. An autoclave is a special pressure vessel that can withstand and control a certain temperature and pressure range. The blank is laid on the surface of a mold with a release agent, and then covered with a porous anti-stick cloth (film), absorbent felt, and breathable felt in sequence, and sealed in a vacuum bag, and then placed in the autoclave. Before heating and curing, the bag is evacuated to remove air and volatiles, and then the temperature is raised, pressure is increased, and curing is carried out according to the curing regime of different resins.

[0003] However, it still has some drawbacks. For example, when the existing autoclave is used to put the blank into the autoclave, it is necessary to use an auxiliary support to push the blank into the autoclave for heating, pressurization and curing. Since the auxiliary support is long, it requires multiple people to operate, which is inconvenient. In addition, the auxiliary support and the autoclave are not designed as a whole, and it will occupy a lot of space when not in use, which cannot make full use of the space.

[0004] To address the aforementioned issues, this application proposes a spacecraft landing gear forming device. Summary of the Invention

[0005] The purpose of this utility model is to provide a spacecraft landing gear forming device to solve the problems mentioned in the background art. In the existing autoclave, when the blank is put into the autoclave, it is necessary to use an auxiliary support to push the blank into the autoclave for heating, pressurization and curing operations. Because the auxiliary support is long, it requires multiple people to operate, which is inconvenient. In addition, the auxiliary support and the autoclave are not integrated, which occupies a lot of space when not in use, and cannot make full use of the space.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a spacecraft landing gear forming device, comprising a thermoplastic tank, a base fixedly connected to the lower outer surface of the thermoplastic tank, a tank door detachably connected to the front outer surface of the thermoplastic tank, a blank placement platform movably connected to the inner wall of the thermoplastic tank, a slide rail fixedly connected to the inner wall of the thermoplastic tank, a sliding connection between the blank placement platform and the slide rail, and a support component provided on the lower outer surface of the blank placement platform.

[0007] Preferably, the support assembly includes a connecting plate, a first groove, a first connecting block, a sleeve, a support rod, a fixed positioning rod, a fixed positioning hole, a limiting block, a limiting hole, a second connecting block, a first roller, a positioning pin, a second groove, and a second roller. The connecting plate is fixedly connected to the outer surfaces of the left and right sides of the blank placement platform, and a first groove is provided on one outer surface of the connecting plate.

[0008] Preferably, a connecting block is movably connected to the inner surface of the groove, a sleeve is fixedly connected to the lower outer surface of the connecting block, and a support rod is movably connected to the lower outer surface of the sleeve.

[0009] Preferably, a fixed positioning rod is movably connected to the outer wall of the support rod, a fixed positioning hole is opened on the outer wall of the sleeve, and the fixed positioning rod is engaged and connected to the inner wall of the fixed positioning hole.

[0010] Preferably, a limiting block is fixedly connected to one side of the outer surface of the first connecting block, a limiting hole is formed on the front outer surface of the limiting block, a second connecting block is fixedly connected to the lower outer surface of the support rod, and a first roller is movably connected to the rear outer surface of the second connecting block.

[0011] Preferably, a positioning pin is provided on the outer surface of the front end of the connecting plate, and one end of the outer wall of the positioning pin is sleeved in the inner wall of the limiting hole. A second groove is provided on the outer surface of the front end of the connecting plate, and a second roller is movably connected to the inner surface of the second groove.

[0012] Compared with the prior art, the beneficial effects of this utility model are: This invention utilizes a support assembly. First, the entire blank placement platform is manually pulled. During this pulling process, the sleeve, support rod, and roller are placed on the ground. The support rod is then fixed in the sleeve by a positioning rod. Next, a positioning pin is inserted into the limiting hole on the limiting block, restricting the support rod at a right angle below the connecting plate. When the blank placement platform needs to retract into the autoclave, simply push the platform manually, pull the positioning pin out of the limiting hole, and retract the support rod into the sleeve. During this pushing process, the platform automatically retracts into the groove, allowing it to fit into the autoclave. This facilitates supporting the protruding platform, placing the blank, and then retracting it into the autoclave. The operation is convenient and simple, reducing the space occupied by auxiliary supports and maximizing space utilization. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of a spacecraft landing gear forming device according to the present invention; Figure 2 This is a schematic diagram of the blank placement platform in a spacecraft landing gear forming device according to the present invention; Figure 3 This is a schematic diagram of the support component in a spacecraft landing gear forming device according to the present invention; Figure 4 This is a side view of a support component in a spacecraft landing gear forming device according to the present invention. Figure 5 This is a partial enlarged view of A in a spacecraft landing gear forming device according to this utility model.

[0014] In the diagram: 1. Autoclave; 2. Base; 3. Door; 4. Blank placement platform; 5. Support assembly; 6. Slide rail; 7. Connecting plate; 8. Groove 1; 9. Connecting block 1; 10. Sleeve; 11. Support rod; 12. Fixed positioning rod; 13. Fixed positioning hole; 14. Limiting block; 15. Limiting hole; 16. Connecting block 2; 17. Roller 1; 18. Positioning pin; 19. Groove 2; 20. Roller 2. Detailed Implementation

[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0016] Please see Figures 1-5This utility model provides a technical solution: a spacecraft landing gear forming device, including a thermostatic tank 1, a base 2 fixedly connected to the lower outer surface of the thermostatic tank 1, a tank door 3 detachably connected to the front outer surface of the thermostatic tank 1, a blank placement platform 4 movably connected to the inner wall of the thermostatic tank 1, a slide rail 6 fixedly connected to the inner wall of the thermostatic tank 1, a sliding connection between the blank placement platform 4 and the slide rail 6, and a support component 5 provided on the lower outer surface of the blank placement platform 4. Its overall structure is simple and easy to operate.

[0017] In this embodiment, as Figures 2-5 As shown, the support assembly 5 includes a connecting plate 7, a groove 8, a connecting block 9, a sleeve 10, a support rod 11, a fixed positioning rod 12, a fixed positioning hole 13, a limiting block 14, a limiting hole 15, a connecting block 16, a roller 17, a positioning pin 18, a groove 19, and a roller 20. The connecting plate 7 is fixedly connected to the outer surfaces of the left and right sides of the blank placement platform 4. A groove 8 is provided on one outer surface of the connecting plate 7. Through the groove 8, the sleeve can be easily inserted. The support rod 11 and the sleeve 10 retract into the groove 8. A connecting block 9 is movably connected to the inner surface of the groove 8. A sleeve 10 is fixedly connected to the lower outer surface of the connecting block 9. The support rod 11 is movably connected to the lower outer surface of the sleeve 10. The sleeve 10 and support rod 11 allow for easy retraction of the support rod 11 into the sleeve 10. A fixing and positioning rod 12 is movably connected to the outer wall of the support rod 11. The outer wall of the sleeve 10 has an opening... The device has a fixed positioning hole 13, and the fixed positioning rod 12 is engaged in the inner wall of the fixed positioning hole 13. The fixed positioning rod 12 allows the support rod 11 to be easily positioned in the inner wall of the sleeve 10. A limiting block 14 is fixedly connected to one side of the outer surface of the connecting block 11. A limiting hole 15 is opened on the outer surface of the front end of the limiting block 14. A connecting block 2 16 is fixedly connected to the outer surface of the lower end of the support rod 11. A roller 17 is movably connected to the outer surface of the rear end of the connecting block 2 16. The roller 17 allows for more flexible pushing of the entire blank placement platform 4. A positioning pin 18 is passed through the outer surface of the front end of the connecting plate 7, and one end of the positioning pin 18 is sleeved in the inner wall of the limiting hole 15. A groove 2 19 is opened on the outer surface of the front end of the connecting plate 7. A roller 20 is movably connected to the inner surface of the groove 2 19. The roller 20 allows for easier sliding of the connecting plate 7 and the slide rail 6.

[0018] Working Principle: A spacecraft landing gear forming device. In use, firstly, the entire blank placement platform 4 is manually pulled using the set support assembly 5. During this pulling process, the sleeve 10, support rod 11, and roller 17 are placed on the ground. The support rod 11 is then fixed in the sleeve 10 using the fixed positioning rod 12. Next, the positioning pin 18 is inserted into the limiting hole 15 on the limiting block 14, restricting the support rod 11 at a right angle below the connecting plate 7. When the blank placement platform 4 needs to retract into the autoclave 1, simply push the blank placement platform 4 manually to move the positioning pin 18 from the limiting hole 15. Pulling out the support rod 11 from the hole 15 and retracting it into the sleeve 10, the support rod 11 will automatically retract into the groove 8 during the pushing process, allowing the blank placement platform 4 to retract into the autoclave 1. This makes it convenient to support the protruding blank placement platform 4 and place the blank in place before retracting it into the autoclave 1. The operation is convenient and simple, and it can reduce the space occupied by the auxiliary support, making full use of all the space. Finally, the detachable door 3 at the front end of the autoclave 1 is closed, and a series of operations such as heating, pressurizing and curing are performed on the blank on the blank placement platform 4.

[0019] Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

Claims

1. A spacecraft landing gear forming apparatus comprising a hot press tank (1), characterised in that: The lower outer surface of the autoclave (1) is fixedly connected to a base (2), the front outer surface of the autoclave (1) is detachably connected to a door (3), the inner wall of the autoclave (1) is movably connected to a blank placement platform (4), the inner wall of the autoclave (1) is fixedly connected to a slide rail (6), the blank placement platform (4) and the slide rail (6) are slidably connected, and the lower outer surface of the blank placement platform (4) is provided with a support component (5).

2. The spacecraft landing gear forming device according to claim 1, characterized in that: The support assembly (5) includes a connecting plate (7), a groove (8), a connecting block (9), a sleeve (10), a support rod (11), a fixed positioning rod (12), a fixed positioning hole (13), a limiting block (14), a limiting hole (15), a connecting block (16), a roller (17), a positioning pin (18), a groove (19), and a roller (20). The connecting plate (7) is fixedly connected to the outer surfaces of the left and right sides of the blank placement platform (4). A groove (8) is provided on one outer surface of the connecting plate (7).

3. A spacecraft landing gear forming apparatus as claimed in claim 2, wherein: The inner surface of the groove (8) is movably connected to the connecting block (9), the lower outer surface of the connecting block (9) is fixedly connected to the sleeve (10), and the lower outer surface of the sleeve (10) is movably connected to the support rod (11).

4. The spacecraft landing gear forming apparatus of claim 2, wherein: The outer wall of the support rod (11) is movably connected to a fixed positioning rod (12), and the outer wall of the sleeve (10) is provided with a fixed positioning hole (13), and the fixed positioning rod (12) is engaged and connected to the inner wall of the fixed positioning hole (13).

5. The spacecraft landing gear forming device according to claim 2, characterized in that: A limiting block (14) is fixedly connected to one side of the outer surface of the connecting block (9). A limiting hole (15) is opened on the front end outer surface of the limiting block (14). A connecting block (16) is fixedly connected to the lower end outer surface of the support rod (11). A roller (17) is movably connected to the rear end outer surface of the connecting block (16).

6. The spacecraft landing gear forming apparatus of claim 2, wherein: The front outer surface of the connecting plate (7) is provided with a positioning pin (18), and one end of the positioning pin (18) is sleeved in the inner wall of the limiting hole (15). The front outer surface of the connecting plate (7) is provided with a groove (19), and the inner surface of the groove (19) is movably connected with a roller (20).

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