Satellite yaw controlling and guiding method

A yaw control and satellite technology, which is applied in the direction of aerospace vehicle guidance devices, aerospace equipment, space navigation equipment, etc., can solve the problem of unfavorable whole-star thermal control, affecting the accuracy of ground orbit determination, and the unsatisfactory accuracy of sailboards to the sun Requirements and other issues to achieve the effect of meeting the daily accuracy requirements and facilitating the implementation of thermal control

Inactive Publication Date: 2016-05-04
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology

In the process of attitude stabilization, the accuracy of the sailboard to the sun cannot meet the requirements
[0004] The traditional method to solve the above problems is to perform yaw control when the β angle is greater than 5°, according to figure 1 The target attitude angle adjusts the satellite attitude; when the β angle is less than or equal to 5°, the yaw adjustment is not performed, the satellite is sta

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  • Satellite yaw controlling and guiding method
  • Satellite yaw controlling and guiding method
  • Satellite yaw controlling and guiding method

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Embodiment Construction

[0019] The specific implementation of a satellite yaw control and guidance method provided by the present invention will be described in detail below by taking a certain high-orbit inclined-orbit satellite as a typical example and referring to the accompanying drawings.

[0020] The satellite is an inclined geosynchronous orbit satellite with an orbital inclination of 55°. The one-dimensional rotating sailboard of the satellite is installed on the ±Y plane of the satellite. Through the adjustment of the yaw attitude and the rotation of the sailboard, the normal line of the sailboard points to the sun, and the accuracy of the sun is 3 ° within.

[0021] The satellite adopts yaw guidance strategy such as image 3 shown. Using this strategy, the obtained on-orbit yaw target attitude and satellite attitude change curves are as follows: Figure 4 As shown, the torque command distribution of the reaction wheel is as follows Figure 5 As shown, the curve of sailboard rotation chan...

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Abstract

The invention provides a guide rule designing method in yaw gesture control over a satellite. The method comprises the following steps that firstly, the track solar angle (an angle beta for short) and a sun vector under a track system are calculated; secondly, when the angle beta is larger than or equal to a given threshold value, a target yaw angle is calculated according to a current track system sun vector, and when the angle beta is smaller than the given threshold value, the target yaw angle is calculated according to a hypothesis sun vector with the angle beta being an assigned angle; thirdly, when the angle beta crosses zero and when it is met the condition that the target yaw angle is a small angle at the same time, a calculation method of the target yaw angle is switched.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, and relates to a guidance law design method when a satellite performs yaw attitude control. Background technique [0002] Due to the large variation range of β angle of satellites in inclined orbit, in order to meet the energy demand, one-dimensional rotating solar panels are usually installed on the satellites. . [0003] During the long-term steady-state operation of the satellite, the reaction wheel is usually used for attitude control. By controlling the yaw attitude, the sun vector is controlled in the XOZ plane of the star and the +X axis of the satellite points to the sun. But when the β angle is small (that is, the sun, the earth and the satellite are close to one line), the maximum angular velocity of the target attitude change reaches more than 10° / s. like figure 1 Shown is a schematic diagram of the change of the satellite target yaw attitude angle in one orbit u...

Claims

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Application Information

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IPC IPC(8): B64G1/36
CPCB64G1/363
Inventor 白涛熊淑杰张锐王昊光刘伟李笑月
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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