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Method and System for Controlling Satellite from Arbitrary Attitude to Sun Orientation

A control method and satellite technology, which is applied in transportation and packaging, space navigation equipment, space navigation aircraft, etc., can solve the problems of no description or report found, no data collected, etc., and achieve the effect of improving control accuracy

Active Publication Date: 2019-12-20
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] 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.

Method used

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  • Method and System for Controlling Satellite from Arbitrary Attitude to Sun Orientation
  • Method and System for Controlling Satellite from Arbitrary Attitude to Sun Orientation

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Embodiment Construction

[0036] The specific embodiments of the present invention will be further described below in conjunction with the drawings.

[0037] Such as figure 1 As shown, when a three-axis stabilized satellite loses its attitude reference and performs full attitude acquisition, the first thing to do is to control the satellite's solar array to orient to the sun. The invention discloses a method for controlling a satellite from an arbitrary attitude to an orientation toward the sun. The control method specifically includes the following steps:

[0038] S1. Use the inertial reference unit to measure the inertial angle increment of the satellite, and obtain the inertial angular velocity after differentiation.

[0039] S2. Use the 0-1 solar sensor to measure the specific position of the sun on the star, and control the satellite to rotate around the X and Z axis to capture the sun according to the solar azimuth signal output by the 0-1 solar sensor, so that the star has the sun in the -Y direction...

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Abstract

The invention discloses a method for controlling a satellite from any attitude to a sun pointing attitude. The method for controlling the satellite from any attitude to the sun pointing attitude comprises the steps of measuring inertial angle increment by using an inertial reference unit; differentiating the inertial angle increment to obtain inertial angular velocity; measuring the specific direction of the satellite where the sun appears by using a 0-1 type sun sensor and carrying out sun acquisition to obtain a sun direction signal; controlling satellite attitude acquisition by using the change of the sun direction signal; and reducing an included angle between sun vector and one axis of the satellite so as to carry out sun pointing. By using the sun direction information of the 0-1 type sun sensor, the sun can be acquired; and through the change of the sun direction signal, the satellite can be controlled to point the sun to provide satellite guarantee for energy supply of the whole satellite; and beneficial effects of realizing the satellite from any attitude to the sun pointing attitude only by using the inertial reference unit and the 0-1 type sun sensor, improving the satellite attitude control accuracy and so on are achieved.

Description

Technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a method and system for controlling a three-axis stabilized satellite from any attitude to the orientation to the sun. Background technique [0002] During the operation of the three-axis stabilized satellite, the attitude may lose its reference. At this time, the attitude control system will work in the full attitude acquisition mode. The basic function of full attitude capture is to realize the orientation of the star to the sun, that is, the normal direction of the solar cell array is basically the same as the direction of the sun vector. [0003] At present, satellites generally use a 0-1 type solar sensor to capture the sun in the direction of the sun, so that the solar cell array has solar signals. However, due to the relatively large field of view of this 0-1 type solar sensor, it is generally not satisfactory. The light conditions of the solar cell array requ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/28B64G1/36
CPCB64G1/24B64G1/28B64G1/363
Inventor 王新吴敬玉林荣峰张艳召陈秀梅
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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