Geostationary orbit large aperture optical imaging satellite payload shade design method

Abstract

A method for designing a load shade of geostationary orbit large-aperture optical imaging satellite includes such steps as: analyzing whether that key part of the load is illuminate or not and analyzing the shielding effect under different incident angles of sunlight by treating the limited characteristic points of the edge of the shade and the inner shade of the load, and calculating the shadingeffect under different incident angles of sunlight. 2, establishing a satellite yaw angle optimization algorithm to obtain an optimal yaw angle; 3, according to that optimal yaw offset angle, the total width of the sunshade being minimized by a three-plate bending design, the requirements of solar protection of satellite load and envelope size of the whole satellite are finally met, and the totalmass of the sunshade is ensure to be minimized at the same time.

Description

technical field [0001] The invention relates to the technology of the payload subsystem and the attitude control subsystem of a space vehicle, and in particular relates to a novel method for designing a sun visor for a payload of a geostationary orbit large-aperture optical imaging satellite. Background technique [0002] In recent years, large-aperture (optical camera aperture exceeding 3m) optical imaging satellites in geostationary orbit have developed rapidly. Compared with low-orbit high-resolution optical imaging satellites, this type of satellite has the characteristics of staying above the equator for a long time and running synchronously with the earth's rotation, which is very conducive to long-term imaging of fixed areas. The orbit height of the geostationary orbit reaches 35,788km. In order to achieve an imaging capability similar to that of low-orbit high-resolution optical imaging satellites, its payload aperture has been greatly increased. Optical imaging loa...

AI Technical Summary

Problems solved by technology

At the same time, due to the constraints of the geometric relationship between the star, the earth, and the sun, the geostationary orbit large-aperture optical imaging satellite inevitably has the problem of direct illumination at midnight: that is, when the satellite is at the sub-satellite point, the sunlight around midnight may directly illuminate the inner wall of the hood inside the payload. Thereby reducing the detection effect and even causing the load to fail to work during this period of time

[0003] At present, there is no description or report of the similar technology of the present invention, and no similar data at home and abroad have been collected yet.

Images