Fastening structure and fastening method of transparent part of observation window of manned spacecraft

Abstract

The invention discloses a fastening structure for a transparent part of an observation window of a manned spacecraft, which comprises a spacecraft casing and a transparent part of the observation window installed on the casing; In the installation structure of the housing, the frame includes a pressing component and a fastening component, and the fastening component is pressed to generate prestress through the cooperation of the pressing component and the transparent part, thereby fastening the transparent part. The fastening structure of the transparent part of the observation window of the manned spacecraft of the present invention forms a whole force-bearing structure of the transparent part and the shell by generating a circle of prestressed structural frame around the transparent part of the observation window, and the edge section of the transparent part is obtained. Effective protection without direct contact with the shell, can effectively transfer the pressure difference and other loads borne by the transparent part to the shell through the prestressed structural frame, ensuring the integrity and stability of the observation window structure, and at the same time, the sealing performance is better. Longer service life.

Description

technical field [0001] The invention relates to various manned spacecraft in the field of national defense construction, in particular to a fastening structure and a fastening method for a transparent part of an observation window of a manned spacecraft. Background technique [0002] In recent years, with the development of science and technology and the needs of national defense, scientific research and other undertakings, countries around the world have increased investment in the development and construction of manned spacecraft, space shuttles, aerospace planes, space stations and other manned spacecraft. Among them, the observation window is a key structural component of a manned spacecraft. In addition to having good optical properties, the safety performance such as pressure resistance and air tightness mainly depends on the fast connection between the transparent part of the observation window and the spacecraft shell. [0003] In order to meet the requirements of th...

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Problems solved by technology

[0006] 1. In the process of manufacturing and processing, there will be more or less certain defects or residual stress in the transparent part of the observation window, which will damage the internal stress balance of the transparent part itself; the subsequent transportation, storage or assembly process may cause This defect or stress is gradually enlarged, and there will be a greater safety hazard in the future

[0007] 2. The arc shape has higher requirements on the processing technology of transparent parts. There must be certain errors in the processing size or radian of transparent parts. Similarly, there is a flatness error in the contact surface between the spacecraft shell and the transparent part. The flange ring and the transparent part have flatness errors. There is also a certain degree of flatness error on the contact surface at the joint of the transparent part. In addition, there are differences in the tightening degree of the flange fastening bolts. The above errors will affect the fit between the transparent part and the shell, resulting in difficulty in the installation of the transparent part, or There is stress concentration after installation, and the interchangeability of transparent products is poor

[0008] 3. During use, although there is a rubber pad between the transparent part of the observation window and the spacecraft shell, there will be a huge pressure difference when the spacecraft is running in space, and the elastic deformation of the rubber pad will reach the limit. At this time The cushioning effect of the rubber pad will be lost and only the sealing effect will remain. At this time, the flexible contact between the transparent part and the shell changes from a flexible contact to a rigid contact. In addition, there is a certain precision error between the transparent part and the shell itself, so this rigid contact It is very unfavorable and extremely unstable for the stress state of the transparent part, and its internal processing stress and installation stress will be amplified, which will further reduce the edge strength of the transparent part until cracks or even damage occur. leading to more serious accidents

[0009] 4. When the manned spacecraft is launching, returning and operating in space, the temperature difference outside the cabin can reach thousands of degrees. In such an environment, the internal stress balance of the transparent part of the observation window will inevitably be destroyed. Once the transparent part itself is in the production or assembly process There are any small flaws or cracks in the glass, which will most likely expand into cracks and even lead to catastrophic accidents such as rupture of transparent parts

[0011] However, with the progress of the times, more and more attention has been paid to the development of manned spaceflight, and people's demand for manned spacecraft is also increasing. However, the core technology that can effectively improve the safety and convenience of spacecraft observation windows has not yet been developed. solve

At present, there is no reasonable solution to this type of problem, and the present invention fills up the gap in this field

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