Orbit element

A proper control strategy controlling the transient orbit element errors to realize the modulation of mean orbit element errors was given .

提出了合适的控制策略，通过对瞬时轨道要素偏差进行控制，实现平均轨道要素偏差的调整目的。

By using the classical orbit element differences method , the periodic characteristics of relative motion and the influence of atmospheric drag on relative motion were analyzed .

基于经典轨道要素偏差法分析了相对运动特性和大气阻力对相对运动的影响。

Comparisons of Pulse Controls for Orbit Element Error Modification

轨道根数偏差修正的脉冲控制比较研究

Based on the precision dynamics model of formation flying that describe the relative movement , each formation flying satellite orbit element is designed .

采用精确描述相对运动的编队飞行运动学模型，设计编队飞行各卫星轨道参数。

Autonomous Relative Orbit Determination for Satellite Formation Flying on basis of Orbit Element Differences

基于轨道根数差的卫星编队自主定轨研究