A method for generating a payload adaptation structure for a satellite system

Abstract

A method for generating a load adaption structure for a satellite system comprises the first step of laying webs, i.e., a plurality of C-shaped webs are spliced into one or more sealed areas; the second step of generating arc edges of the sealed areas of the adaption structure by laying C-shaped webs on the corresponding C-shaped webs in the same direction, and generating straight edges of the sealed areas of the adaption structure by splicing C-shaped webs on the corresponding C-shaped webs in the reverse direction; and the third step of assembling the sealed areas into the shape of the adaption structure, and laying wing plates on all the straight edges and arc edges of the adaption structure. According to the third step, the wing plates in a bearing area are continuously laid in multiple layers in different directions, and the wing plates in a non-bearing area are provided with breaking points which are located on the same layers and in different directions. By means of the method, the size stability and the bearing mass ratio of the load adaption structure after long-time use in orbit are improved, and mounting foundation faces are provided for large loads such as cameras.

Description

technical field [0001] The invention belongs to the field of spacecraft structures, in particular to a method for generating a load adaptation structure for a satellite system. Background technique [0002] When the spacecraft is in orbit, it is in a high vacuum, alternating cold and heat environment, and is damaged and destroyed by various space factors such as cosmic rays, solar radiation, high-energy particles, plasma, atomic oxygen, etc., which seriously threatens the on-orbit spaceflight. device reliability and security. Space environmental factors cause changes, damage, and even destruction of spacecraft material properties in different ways, resulting in changes in the basic properties of materials such as mechanical properties and thermal expansion coefficients, which in turn affect the performance of high-precision loads on some stars, such as high-resolution earth observation satellite cameras. The imaging accuracy of the spacecraft is even a serious threat to the...

AI Technical Summary

Problems solved by technology

[0005] (1) Most of these supporting structures are metal brackets - poor dimensional thermal stability and low load-bearing mass ratio;

[0006] (2) Existing composite supports mostly use quasi-isotropic laminates, which do not take advantage of the designable characteristics of composite structures. In addition, in terms of high stability design, many structures are more about ensuring the stability of one dimension, such as each This kind of rod, beam and other structures only ensure the minimum dimensional deformation in one direction of the length, and do not achieve the same effect in the other two dimensions

However, with the improvement of user requirements for observation accuracy, especially for cameras and payloads with high requirements for pointing accuracy, these loads have high requirements for on-orbit pointing accuracy, and they need to be kept stable for a long time in orbit. However, the existing technology No relevant information has been found to achieve the above purpose

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