利用球面三角形的几何关系进行了基于STK（卫星工具包）的小卫星轨道交会的规划和设计。
Small satellite orbital rendezvous is designed using the geometric logic of spherical triangle and the STK (Satellite Tool Kit) software.
本文将一种有效的自适应滤波方案成功地应用于地球同步卫星轨道交会时的状态估计与参数估计之中。
An efficient adaptive filtering scheme is successfully used in the state and parameter estimation for the orbital rendezvous of earth synchronous satellites.
理论分析和仿真结果表明，该控制律的交会精度较高、计算量小，可实现轨道交会控制的自主性和快速性。
The theoretic analysis and simulation result showed that this control law had high orbit rendezvous precision with little calculation, which could realize fast and automatic orbit rendezvous.
空间交会对接涉及到两个航天器同时要进行多达12个自由度的轨道和姿态控制问题。
The rendezvous and docking (RVD) between two spacecrafts in space involves both orbit control and attitude control with up to 12 degrees of freedom.
考虑能量、时间、视线等约束条件，基于微分方程法研究了近程自主交会滑移轨道设计方法。
Considering constraints of energy, time and line-of-sight angle, a near-range autonomous rendezvous glidescope orbit design method is studied based on the differential equation method.
本文介绍了将智能控制方法用于航天器交会对接段的轨道控制。
The method of intelligent control applied to the orbital control of rendezvous and docking phase of spacecraft is presented in this paper.
采用线性化CW方程研究了空间飞行器近程自主交会轨道设计问题。
Near-field autonomous rendezvous orbit design problem is discussed by adopting CW equation in the paper.
将准最优控制理论用于轨道自主快速交会时线性二次型调节器的设计。
The hypo-optimal theory was applied on the design of linear quadratic regulator for fast and automatic orbit rendezvous in this paper.
采用精确轨道动力学模型，得到了满足共面交会约束的发射窗口，以及地月转移轨道特性。
The launch window meeting the restriction of coplanar rendezvous and the characteristics of trans-lunar trajectory is obtained by precise dynamics model.
研究了标称飞行轨道最优交会点选取，交会时间与发射时间计算等问题。
The ideal rendezvous time, launch time and rendezvous point in space were studied.
提出了一种在缺少绝对轨道信息时的航天器椭圆轨道自主交会方法。
An approach for spacecraft autonomous rendezvous in an elliptical orbit without orbit information is developed.
算法能够以较省的燃料消耗实现轨道面内任意方向、任意时间内满足约束的近距离交会。
The other scenarios illustrate that the guidance algorithm can ensure a close range rendezvous motion in any direction, at any time with the fuel economy and under the constraints as well.
所提出的计算模型、控制策略和分析方法适用于目标飞行器交会对接轨道设计和控制实施。
The proposed model, control strategy and analysis methods are applicable to the target′s rendezvous orbit design and control implementation.
根据目标飞行器轨道高度和追踪飞行器入轨轨道高度，给出了目标飞行器交会对接轨道初始相位的设计方法。
According to the target spacecraft's orbit height and the chaser spacecraft's orbit height, the design method of the target's initial phase for the rendezvous orbit was presented.
根据目标飞行器轨道高度和追踪飞行器入轨轨道高度，给出了目标飞行器交会对接轨道初始相位的设计方法。
According to the target spacecraft's orbit height and the chaser spacecraft's orbit height, the design method of the target's initial phase for the rendezvous orbit was presented.
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