The invention discloses a satellite formation configuration target perturbation self-adaptive correction high-precision keeping method, which comprises the steps of establishing a satellite formation configuration shot divergence model based on a near-circular orbit E/I vector relative motion equation; establishing an eccentricity rate vector configuration target prediction model based on a satellite formation configuration forming mechanism and a shot divergence characteristic; based on a divergence principle of formation configuration parameters, establishing a prediction model of a formation configuration target semi-major axis difference; and based on a Gaussian perturbation equation, designing a fuel optimal two-pulse position control scheme in a formation configuration plane, and based on the fuel optimal two-pulse position control scheme, carrying out adaptive correction on a satellite formation configuration target. Through the control target prediction method adopting formation configuration shot divergence compensation, the problem that partial parameters of a two-pulse ignition control strategy cannot be accurately controlled is solved, and the effects that the two-pulse ignition frequency is low and the control period is long are achieved.
本发明公开了一种卫星编队构形目标摄动自适应修正高精度保持方法,包括:基于近圆轨道E/I向量相对运动方程,建立卫星编队构形受摄发散模型;基于卫星编队构形形成机理及受摄发散特性,建立偏心率矢量构形目标预测模型;基于编队构形参数的发散原理,建立编队构形目标半长轴差的预测模型;基于高斯摄动方程,对编队构形平面内的燃料最优两脉冲位置控制方案进行设计,基于燃料最优两脉冲位置控制方案对卫星编队构形目标进行自适应修正。通过采用编队构形受摄发散量补偿的控制目标预测方法,解决了两脉冲点火控制策略部分参数不可精确控制的问题,实现了两脉冲点火频率低且控制周期长的效果。
Satellite formation configuration target perturbation adaptive correction high-precision keeping method
一种卫星编队构形目标摄动自适应修正高精度保持方法
2022-09-06
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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