High-accuracy micro deformation star sensor mounting bracket

Abstract

The invention discloses a high-accuracy micro deformation star sensor mounting bracket. A star sensor mounting plate is connected to the outer surface of a thin-wall shell structure; a heat pipe is positioned inside the thin-wall shell structure; one end of the heat pipe is connected to the star sensor mounting plate; the other end of the heat pipe is connected with a heat collecting plate; the heat collecting plate is connected to the inner side of the top of the thin-wall shell structure and partially extends out of the top of the thin-wall shell structure; a first insulation mat is mounted between the heat collecting plate and the thin-wall shell structure; a rear cover board is connected to the back of the thin-wall shell structure so as to form a mounting bracket head; one end of a strut assembly is connected with the mounting bracket head; the other end of the strut assembly is used for mounting a spacecraft optical imaging effective load structure body. The high-accuracy micro deformation star sensor mounting bracket solves the technical difficult problem of harsh thermal deformation of a high-orbit spacecraft star sensor mounting bracket so as to meet the requirements on high-accuracy attitude determination of a spacecraft and image navigation registration, and meanwhile, has the advantages of novel structural form, light weight and the like.

Description

technical field [0001] The invention relates to a device in the field of spacecraft structure design, in particular to a mounting bracket for a high-precision micro-deformation star sensor. Background technique [0002] The installation of star sensors for spacecraft is not directly installed on the structure of the spacecraft body, and often requires the transfer of a special installation structure. The installation structure provides an instrument mounting surface and a mounting surface with the spacecraft structure body. Conventional installation structures generally require light weight, high rigidity, good electrical conduction and heat transfer characteristics, and sufficient strength, so they are often machined from lightweight aluminum alloy or magnesium alloy materials. When the spacecraft is in orbit, these installation structures are in a harsh environment that alternates repeatedly. Due to the high thermal expansion rate of the metal material, the installation st...

AI Technical Summary

Problems solved by technology

[0004] The invention proposes a high-precision micro-deformation star sensor mounting bracket in view of the fact that the traditionally designed star sensor installation structure cannot meet the high-precision attitude determination of high-orbit spacecraft and the lack of image navigation registration requirements, in which the star sensor mounting plate passes through The heat pipe dissipates heat, and at the same time, it is connected with the heat pipe through a flexible device, so that it has both good thermal conductivity and thermal deformation isolation. At the same time, the thin-walled cavity structure and rod components are made of carbon fiber composite materials to ensure that the device has both large Rigidity and light weight

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