General Design Method of Attitude Reference for Multiple Working Modes of Agile Satellites

A working mode and general-purpose design technology, applied in space navigation equipment, space navigation equipment, space navigation aircraft, etc., can solve the problems of many program flow branches, poor versatility, and complex testing, so as to achieve less program flow branches and faster testing. Easy, Versatile Effects

Active Publication Date: 2022-04-22
SHANGHAI AEROSPACE CONTROL TECH INST
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AI Technical Summary

Problems solved by technology

If the traditional design method of conventional satellites needs to establish multiple attitude control datums, when the number of payloads and targets is large, the attitude datum design algorithm will increase rapidly, resulting in more branches of the finalized program flow, complex testing, and poor versatility

Method used

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  • General Design Method of Attitude Reference for Multiple Working Modes of Agile Satellites
  • General Design Method of Attitude Reference for Multiple Working Modes of Agile Satellites
  • General Design Method of Attitude Reference for Multiple Working Modes of Agile Satellites

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Experimental program
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Embodiment

[0037] 1. Determine the space reference vector by the target position of the given J2000.0 inertial coordinate system.

[0038] For the ground target vector, the spatial physical relationship determines the normal of the satellite's orbital plane (the pitch axis Y of the orbital coordinate system o ) will not be close to parallel with it (the included angle range is not 90±70 degrees); for the analysis of the positions of multiple space objects, if the space objects are not located in the ±20 degree cone of the normal of the satellite orbit plane, then it can be Determine the normal of the satellite’s orbital plane as the space reference vector, which is suitable for establishing attitude references for all target points; if multiple space targets are located within ±20° of the normal of the satellite’s orbital plane, it is necessary to determine another A vector perpendicular to the normal of the orbital surface, such as the flight direction of the satellite orbit (the rollin...

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Abstract

The invention discloses a general design method for attitude references of multiple working modes of an agile satellite, which comprises the following steps: determining the space reference vector according to the spatial distribution of the satellite to the target vector, establishing the satellite target coordinate system, and obtaining the reference coordinate system to the satellite target coordinate system The attitude quaternion of the load pointing to the target is obtained, which is used as the attitude reference of the satellite attitude control. Compared with the prior art, the present invention provides a general design method of the attitude reference, and the control attitude reference applicable to multi-load and multi-target pointing tasks can be obtained by using this method. The design algorithm is simple, the program flow has few branches, and the test is easy. And strong versatility.

Description

technical field [0001] The invention relates to a general design method for attitude references in multiple working modes of an agile satellite, and belongs to the technical field of satellite attitude control. Background technique [0002] With the diversification of space missions, higher requirements are put forward for the rapid maneuverability and multi-task adaptability of the satellite attitude control system. Satellites with rapid maneuverability are called agile satellites. For agile satellites, in different tasks, it is necessary to maneuver the satellite body attitude to make its load point to different targets as required. The attitude control task of conventional satellites is generally to control the pointing of a single or at most two or three targets. The installation method and the spatial position of its target can establish their own attitude control benchmarks. For agile satellites with multi-target pointing tasks, it is not only necessary to point to mu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 杜宁陈文晖王世耀徐家国孙杰查理吕若宁高四宏
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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