提出了一种通过控制平均轨道控制目标对应的瞬时轨道偏差量进行轨道修正的方法。
An orbital modulation method by controlling the corresponding transient orbit errors of mean orbit control targets was proposed.
在解析轨道理论基础上，给出了平均轨道要素偏差到瞬时轨道要素偏差的状态转移矩阵。
On the basis of analytical orbit theory, the state transition matrix from mean to transient orbit errors was put forward.
在解析轨道理论基础上，给出了平均轨道要素偏差到瞬时轨道要素偏差的状态转移矩阵。
On the basis of analytical orbit theory, the state transition matrix from mean to transient orbit errors was put forward.
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