Inclined orbit spacecraft energy obtaining method based on yaw steering

Abstract

The invention relates to an inclined orbit spacecraft energy obtaining method based on yaw steering. The inclined orbit spacecraft energy obtaining method based on yaw steering includes the steps of calculating the solar unit vector of a J2000 inertial coordinate system according to Julian century numbers, calculating a solar elevation angle beta according to the solar unit vector, the satellite position and the satellite running speed, calculating a transfer matrix Aoi from the J2000 inertial coordinate system to an orbital coordinate system according to the satellite position and the satellite running speed, calculating the solar angular altitude theta s of the orbital coordinate system according to the solar unit vector and the transfer matrix Aoi from the J2000 inertial coordinate system to the orbital coordinate system, calculating the yaw steering angle psi and a sailboard drive angle R according to the solar elevation angle beta and the solar angular altitude theta s, and enabling the solar vector to be perpendicular to the plane of the solar sailboard through yaw posture control and sailboard one-dimensional driving to ensure that a spacecraft can obtain energy. The normal of the solar sailboard of the spacecraft can point to the sun under the situation of the large change range of the solar elevation angle and the complex lighting condition, so that it is ensured that the spacecraft can obtain solar energy under the situation of an inclined orbit.

Description

technical field [0001] The invention relates to a method for obtaining energy for an inclined-orbit spacecraft based on yaw guidance, which belongs to the research on the attitude control method of an attitude-orbit control system of the spacecraft, and is used to ensure the energy for the inclined-orbit spacecraft. Background technique [0002] At present, most of the energy required by long-lived spacecraft is provided by solar panels. Most of my country's low-orbit long-life spacecraft adopt sun-synchronous orbits. In addition to considering mission requirements, another important reason is to adopt this orbit. The solar panels can obtain better lighting conditions and ensure the energy of the spacecraft. However, with the rapid development of science and technology, the use of inclined orbits to achieve certain specific mission goals has become more advantageous. For example, the use of satellites with an inclination of 75° can achieve optimal coverage of the earth. As ...

AI Technical Summary

Problems solved by technology

That is to say, the sun may appear in various places of the spacecraft, which is not conducive to the directional control of the sailboard to the sun, is not conducive to the thermal control of the whole star, and is not conducive to the layout of the optical attitude sensor

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