Research on Attitude Transformation and Amendment of High Orbit Spacecraft

被引：0
|
作者：
Qi Wei [1 ]
Xu Wei [2 ]
Ding Ran [2 ]
Chen Pei [2 ]
机构：
[1] BITTT, Beijing, Peoples R China
[2] Chinese Acad Sci, Beijing Univ Aeronaut & Astronaut, Beijing UCAS Space Technol CO Ltd, Beijing, Peoples R China
来源：
2014 FOURTH INTERNATIONAL CONFERENCE ON INSTRUMENTATION AND MEASUREMENT, COMPUTER, COMMUNICATION AND CONTROL (IMCCC) | 2014年
关键词：
Aerospace track telemetry and control; High orbit spacecraft; Situation analysis; Transformation of attitude; Error amendment;
D O I：
10.1109/IMCCC.2014.38
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
Based on the spacecraft attitude analysis and display problem in Aerospace track telemetry and control (TT&C) field, an attitude transformation and amendment method of high orbit is proposed. With this algorithm, the theory of full-scale attitude transformation which is defined depending on different rotation ranges is deduced, the attitude error amendment between inertial coordinate system and non-inertial coordinate system is carried out by building the Earth's rotation weighting matrix, and the attitude angles are mapped into the parameters which drive three-dimensional model in the geographic coordinate system. As shown by the simulation and experiment results, this method can effectively restrain the singularity during attitude transformation, amend the drift error due to the Earth's rotation, accurately reflect the spacecraft attitude information under different coordinate systems in the situation analysis display system. This method could meet the universality needs of the aerospace TT&C system, and provide an effective technical approach for the long time and high maneuvering flight experimentation.
引用
收藏
页码：145 / 150
页数：6
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