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Solar cell array control strategy method suitable for yaw maneuvering satellite

A solar cell array and control strategy technology, which is applied to motor vehicles, space navigation equipment, space navigation aircraft, etc., can solve the problems of satellite thermal control, energy and sensor layout difficulties, and achieve the optimization of the entire satellite design scheme, Guaranteed energy effect

Inactive Publication Date: 2017-02-01
SHANGHAI SATELLITE ENG INST
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  • Abstract
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  • Application Information

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Problems solved by technology

This brings great difficulties to satellite thermal control, energy and sensor layout.

Method used

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  • Solar cell array control strategy method suitable for yaw maneuvering satellite

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Embodiment Construction

[0019] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0020] The invention provides a solar cell array control strategy method suitable for yaw maneuvering satellites. By analyzing the orbital illumination conditions of the satellites and combining the different yaw bias states of the satellites, a solar cell array control strategy is designed to achieve Meet satellite energy requirements. It includes the steps of: analyzing the illumination conditions on the orbit where the satellite is located; designing a satellite yaw maneuvering scheme; and designing ...

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Abstract

The invention provides a solar cell array control strategy method suitable for a yaw maneuvering satellite. The method comprises the steps that the light condition of an orbit where the satellite is located is obtained; a satellite yaw maneuvering scheme is determined according to the light condition; and a solar cell array control strategy is obtained according to the satellite yaw maneuvering scheme. The problem of energy of on-orbit flying of the inclined orbit satellite is solved.

Description

technical field [0001] The invention relates to an overall design technology of an inclined orbit satellite, a driving control technology of a solar battery array and an attitude control technology, especially a method for designing a control strategy of a solar battery array according to orbital illumination conditions. Background technique [0002] A satellite runs on an inclined orbit, and its solar altitude angle changes periodically. Satellites do not have relatively fixed backsides. This brings great difficulties to satellite thermal control, energy and sensor layout. The satellite adopts the yaw maneuver scheme to better solve these problems. After adopting the yaw maneuver scheme, the satellite has four bias states in orbit, and the illumination conditions are different in each bias state, so it is necessary to design a solar array drive control strategy for each bias state to ensure that the satellite Energy during orbital flight. Contents of the invention [...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/44
CPCB64G1/443
Inventor 辛岩杨燕叶小舟刘胜崔本杰丰保民叶立军陈占胜赖京
Owner SHANGHAI SATELLITE ENG INST
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