The invention relates to a satellite inertial attitude high-precision prediction method suitable for large time delay, and the method comprises the steps: constructing a projection relation between the motion characteristics of a satellite and a prediction attitude, and carrying out the attitude extrapolation for a dynamic process and a steady-state process through employing a reference attitude linear difference value and adaptive polynomial fitting; high-precision attitude prediction at the dynamic in-place initial stage and in the stable tracking process is achieved, and satellite attitude maneuver and extrapolation precision of the stable tracking process under the condition of large time delay are guaranteed.

    本发明涉及一种适用于大时延的卫星惯性姿态高精度预测方法,该方法构建卫星运动特性与预测姿态的投影关系,针对动态过程和稳态过程分别利用参考姿态线性差值和自适应多项式拟合进行姿态外推,实现动态到位初期及稳定跟踪过程的高精度姿态预测,保证大时延情况下的卫星姿态机动及稳定跟踪过程的外推精度。


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    Title :

    Satellite inertial attitude high-precision prediction method suitable for large time delay


    Additional title:

    一种适用于大时延的卫星惯性姿态高精度预测方法


    Contributors:
    WANG LIJIAO (author) / TAO JIAWEI (author) / CHANG LUONAN (author) / LEI YONGJUN (author) / WANG SHUYI (author) / REN BIN (author) / LYU GAOJIAN (author) / LI JINGXIN (author) / SI ZHUHUA (author)

    Publication date :

    2025-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G01C Messen von Entfernungen, Höhen, Neigungen oder Richtungen , MEASURING DISTANCES, LEVELS OR BEARINGS / B64G Raumfahrt , COSMONAUTICS



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