Screw disengaging preventing structure for large-plane product outside spacecraft cabin and application of screw disengaging preventing structure

Abstract

The invention discloses a screw disengaging preventing structure for a large plane product outside a spacecraft cabin and application of the screw disengaging preventing structure. The screw disengaging preventing structure at least comprises a plane shell, a flange type screw, a limiting nut and a limiting spring. A plurality of stepped mounting holes are formed in the planar shell, and the planar shell is mounted outside an aircraft cabin; the limiting nut is provided with a central through hole, an external thread of the limiting nut is matched with an internal thread at the top of the stepped mounting hole, and the limiting nut is mounted at the top of the stepped mounting hole; the flange type screw is provided with a flange type plane, the flange type screw penetrates through the center through hole, a tool penetrates through the center through hole to disassemble and assemble the flange type screw, and disassembly of the plane shell and the outside of the aircraft cabin is completed; the limiting spring is compressed between the flange type plane and the plane shell, and the flange type screw is prevented from being disengaged. The structure for preventing the screws from falling off is suitable for occasions for preventing the fasteners from falling off during on-track replacement operation of large-plane products.

Description

Technical Field

[0001] The invention relates to the technical field of screw-out prevention structures, and in particular to a screw-out prevention structure for a large flat product outside a spacecraft cabin and application thereof. Background Art

[0002] With the development of aerospace technology, the installation resistance requirements for large heat dissipation surface equipment outside the Chinese space station are getting higher and higher. At the same time, many space exploration missions have put forward the requirements for on-orbit replacement or on-orbit expansion of aircraft. Both on-orbit replacement and on-orbit expansion involve the problem of inability to collect fasteners during on-orbit maintenance, replacement, and disassembly of products. There is a demand for large-surface equipment with high installation rigidity and no need to collect fasteners during disassembly and assembly. Due to the constraints of aircraft equipment layout, equipment configuration and other conditions, it is time-consuming and laborious for astronauts to disassemble and assemble equipment on orbit. Therefore, there is an urgent need for a structure suitable for spacecraft extravehicular equipment to assist astronauts in repairing, replacing and disassembling equipment. Summary of the invention

[0003] The purpose of the present invention is to provide a screw-out prevention structure for large flat products, which can evenly distribute fastening points at multiple points in the large flat equipment to improve the connection stiffness of flat products, and will not cause screws to fall out during product maintenance, replacement and disassembly, thereby avoiding the problem of fastener collection.

[0004] In order to achieve the above-mentioned object, the present invention provides a screw-out prevention structure for a large flat product outside a spacecraft cabin, comprising at least: a flat housing, a flange screw, a limiting nut, and a limiting spring;

[0005] The planar shell is provided with a plurality of stepped mounting holes, and the planar shell is mounted outside the aircraft cabin;

[0006] The limiting nut has a central through hole, the external thread of the limiting nut matches the internal thread at the top of the stepped mounting hole, and the limiting nut is installed at the top of the stepped mounting hole;

[0007] The flange screw has a flange plane, and the flange screw passes through the central through hole. The flange screw is disassembled and assembled by using a tool passing through the central through hole, thereby completing the disassembly of the flat shell and the outside of the aircraft cabin;

[0008] The limit spring is compressed between the flange-type plane and the plane housing to prevent the flange-type screw from falling out.

[0009] Preferably, at least 9 stepped mounting holes are provided on the planar housing.

[0010] Preferably, the structure of the stepped mounting hole matches the structure of the flange screw, so that the flange plane of the flange screw is embedded in the stepped mounting hole.

[0011] Preferably, the surface of the limiting nut further has a slotted groove, and the slotted groove is rotated by a tool so that the external thread of the limiting nut is screwed into the stepped mounting hole.

[0012] Preferably, the flange screw is vertically arranged in the central through hole.

[0013] Preferably, the planar housing has a length of 500 mm and a width of 500 mm.

[0014] Preferably, the length of the flange screw is 35 mm to 37 mm.

[0015] Preferably, the depth of the stepped mounting hole is 23 mm to 25 mm.

[0016] Preferably, the diameter of the central through hole of the limiting nut is 8 mm to 10 mm.

[0017] The present invention also provides an application of the screw-out prevention structure as described above, wherein the screw-out prevention structure is used for on-orbit maintenance, replacement, and disassembly of large planar equipment outside a cabin.

[0018] Compared with the prior art, the beneficial effects of the present invention include at least:

[0019] (1) The planar shell of the anti-screw disengagement structure of the present invention is provided with a plurality of stepped mounting holes, the limiting nut has a central through hole, the external thread of the limiting nut matches the top internal thread of the stepped mounting hole, the flange screw has a flange plane, the flange screw passes through the central through hole, and the flange screw is disassembled and assembled by a tool passing through the central through hole to complete the disassembly of the planar shell and the outside of the aircraft cabin; when the planar shell is not installed outside the aircraft cabin, the limiting spring provides a force for the flange screw, so that the flange screw shrinks in the stepped mounting hole of the planar shell, which is convenient for the installation of the planar shell outside the aircraft cabin; when the planar shell is installed outside the aircraft cabin, the tool passes through the central through hole of the limiting nut to tighten the flange screw, and the limiting spring provides resistance for the flange screw, so that there is an operating force sense and the thread is prevented from loosening when the flange screw is installed, so that the flange screw will not fall off outside the aircraft cabin, thereby improving the installation efficiency.

[0020] (2) The anti-screw structure of the present invention is compact and can realize evenly distributed fastening points at multiple points in a large flat device to improve the connection rigidity of flat products. The anti-screw structure can realize repeated disassembly and assembly of products. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The present invention is a schematic diagram of the appearance of a screw-out prevention structure for a large flat product outside a spacecraft cabin.

[0022] Figure 2 The cross-sectional structure schematic diagram of a screw-out prevention structure for a large flat product outside a spacecraft cabin of the present invention is shown when the flat shell is not installed outside the cabin of the cabin.

[0023] Figure 3 The present invention is a schematic cross-sectional structural diagram of a screw-out prevention structure for a large flat product outside a spacecraft cabin when the flat shell is installed outside the cabin of the aircraft.

[0024] Figure 4 This is an enlarged view of the details of the flat shell and the stepped mounting holes in the screw-out prevention structure for a large flat product outside a spacecraft cabin of the present invention.

[0025] Figure 5 The present invention is a schematic structural diagram of a limiting nut of a screw-out prevention structure for a large flat product outside a spacecraft cabin.

[0026] Figure 6 The present invention is a schematic structural diagram of a flange-type screw of the present invention used for a screw-out prevention structure of a large flat product outside a spacecraft cabin.

[0027] Figure identification: 1-limiting nut, 2-limiting spring, 3-flange screw, 31-flange plane, 4-large plane product housing, 41-stepped mounting hole, 5-aircraft mounting plate, 11-slotted slot, 12-center through hole, 13-external thread. DETAILED DESCRIPTION

[0028] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0029] like Figures 1 to 6As shown, the present invention provides a screw-out prevention structure for large flat products outside the cabin of a spacecraft, which at least comprises: a large flat product housing 4, a flange screw 3, a limit nut 1, and a limit spring 2. Among them, the large flat product housing 4 is provided with a plurality of stepped mounting holes 41, and the large flat product housing 4 is a flat device installed outside the cabin of the aircraft; the surface of the limit nut 1 is provided with a straight groove 11 for rotating it with a tool, and the center of the limit nut 1 has a central through hole 12, and the limit nut 1 also has an external thread 13, and the external thread 13 of the limit nut 1 matches the top internal thread of the stepped mounting hole 41. By rotating the straight groove 11 of the limit nut 1 with a tool, the external thread 13 of the limit nut 1 and the stepped mounting hole 41 can be rotated with each other. The limiting nut 1 is installed on the top of the stepped mounting hole 41, so that the flange screw 3 cannot float around due to weightlessness outside the aircraft cabin, avoiding the collection of fasteners; the flange screw 3 has a flange plane 31, and the flange screw 3 passes through the central through hole 12. The flange screw 3 is disassembled and assembled by a tool through the central through hole 12 to complete the disassembly of the large flat product shell 4 and the outside of the aircraft cabin; the limiting spring 2 is compressed between the flange plane 31 and the large flat product shell 4 to prevent the flange screw 3 from falling out and tilting. In actual application, the large flat product shell 4 is fixed by the aircraft mounting plate 5.

[0030] In some embodiments, in order to tighten and shrink the flange screw 3 in the stepped mounting hole 41 , the structure of the stepped mounting hole 41 matches the structure of the flange screw 3 , so that the flange screw 3 can be embedded in the stepped mounting hole 41 .

[0031] In some embodiments, when the large flat product housing 4 is not installed outside the aircraft cabin, the limit spring 2 provides elastic force for the flange screw 3, so that the flange screw 3 shrinks inside the large flat product housing 4, thereby facilitating the installation of the large flat product housing 4 outside the aircraft cabin.

[0032] In some embodiments, when the large flat product housing 4 is installed outside the aircraft cabin, the limit spring 2 provides resistance for the flange screw 3, so that there is an operating force sense and thread anti-loosening when the flange screw 3 is installed, so the flange screw 3 will not fall off when installed outside the aircraft cabin.

[0033] In some embodiments, the large flat product housing 4 has a length of 500 mm and a width of 500 mm. The length of the flange screw 3 is 35 mm to 37 mm, preferably 37 mm, and the movement hole depth of the flange screw 3 is 12.5 mm. The depth of the stepped mounting hole 41 is 23 mm to 25 mm, preferably 25 mm. The diameter of the central through hole of the limiting nut is 8 mm to 10 mm, and the depth is 18.5 mm.

[0034] The present invention provides a screw-out prevention structure for large flat products outside the cabin of a spacecraft. The structure is suitable for preventing fasteners from falling out during on-orbit replacement operations of large flat products. Due to its compact structure, fastening points can be evenly distributed at multiple points in the large flat product to improve the connection stiffness of flat products. In view of the mechanical resistance requirements for installation and the difficulty of collecting fasteners during maintenance, replacement, and disassembly of large heat dissipation flat equipment outside the cabin of the space station, a new method is provided to solve the problem of astronauts being unable to collect fasteners on orbit during installation and disassembly of extravehicular products, while ensuring the mechanical resistance requirements of large heat dissipation flat equipment. The screw-out prevention structure of the present invention will prevent screws from falling out during product maintenance, replacement, and disassembly outside the cabin of the aircraft, thus avoiding the problem of fastener collection.

[0035] In summary, the anti-screw disengagement structure of the present invention at least includes: a flat shell, a flange screw, a limiting nut, and a limiting spring; the flat shell is provided with a plurality of stepped mounting holes, and the flat shell is installed outside the aircraft cabin; the limiting nut has a central through hole, and the external thread of the limiting nut matches the internal thread at the top of the stepped mounting hole, and the limiting nut is installed at the top of the stepped mounting hole; the flange screw has a flange plane, and the flange screw passes through the central through hole, and the flange screw is disassembled and assembled by a tool through the central through hole, so as to complete the disassembly of the flat shell and the outside of the aircraft cabin; the limiting spring is compressed between the flange plane and the flat shell to prevent the flange screw from disengaging. Fastening points can be evenly distributed at multiple points in large flat products to improve the connection stiffness of flat products, so as to solve the need for on-orbit installation of large heat dissipation surface equipment outside the space station cabin to facilitate installation and operation by astronauts.

[0036] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

Claims

1. A screw-out prevention structure for a large flat product outside a spacecraft cabin, characterized in that: At least include: a flat housing, flange screws, a limit nut, and a limit spring; The planar shell is provided with a plurality of stepped mounting holes, and the planar shell is mounted outside the aircraft cabin; The limiting nut has a central through hole, and the external thread of the limiting nut matches the internal thread at the top of the stepped mounting hole, and the limiting nut is installed at the top of the stepped mounting hole; the flange screw has a flange plane, and the flange screw passes through the central through hole, and the flange screw is disassembled and assembled by using a tool through the central through hole, thereby completing the disassembly of the flat shell and the outside of the aircraft cabin; The limit spring is compressed between the flange-type plane and the plane housing to prevent the flange-type screw from falling out.

2. The screw-out prevention structure according to claim 1, characterized in that: The planar housing is provided with at least 9 stepped mounting holes.

3. The screw-out prevention structure according to claim 1, characterized in that: The structure of the stepped mounting hole matches the structure of the flange screw, so that the flange plane of the flange screw is embedded in the stepped mounting hole.

4. The screw-out prevention structure according to claim 1, characterized in that: The surface of the limiting nut is also provided with a slotted groove, and the slotted groove is rotated by a tool so that the external thread of the limiting nut is screwed into the stepped mounting hole.

5. The screw-out prevention structure according to claim 1, characterized in that: The flange screw is vertically arranged in the central through hole.

6. The screw-out prevention structure according to claim 1, characterized in that: The planar housing has a length of 500 mm and a width of 500 mm.

7. The screw-out prevention structure according to claim 1, characterized in that: The length of the flange screw is 35 mm to 37 mm.

8. The screw-out prevention structure according to claim 1, characterized in that: The depth of the stepped mounting hole is 23 mm to 25 mm.

9. The screw-out prevention structure according to claim 1, characterized in that: The diameter of the central through hole of the limiting nut is 8mm to 10mm.

10. An application of the screw-out prevention structure according to any one of claims 1 to 9, characterized in that: The screw-out prevention structure is used for on-orbit maintenance, replacement, and disassembly of large planar equipment outside the cabin.

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