Non-coplanar orbit rendezvous control algorithm based on fixed-impulse single-pulse

基于定冲量单脉冲的异面轨道交会控制算法

Shanghai Aerospace Control Technology Institute, Shanghai 201100, China

Received: 14 April 2025

Abstract

To address the challenge of precise rendezvous in non-coplanar orbits, this study proposes an orbital maneuver method based on solid propulsion. The relationship between transfer duration and impulse magnitude is analyzed, and under the constraint of fixed impulse magnitude, the correlation between transfer duration and minimum rendezvous error is investigated. The transfer trajectory design problem is ultimately transformed into finding the minimum point of a single-valley function. A control solution framework for non-coplanar orbit rendezvous using fixed-impulse single-pulse propulsion is developed. The proposed workflow involves three key steps: first, calculating the time required for the target to coast inertially to a virtual intersection point; second, employing Lambert's algorithm to determine the minimum velocity increment; and third, integrating the golden section method with an optimal impulse guidance algorithm to precisely solve for transfer duration and impulse direction when the chaser's impulse exceeds the minimum increment. Simulation results demonstrate that the algorithm achieves high computational efficiency and rapid convergence, with a final rendezvous accuracy of 0.6 meters. This approach provides an effective solution for precision rendezvous tasks in non-coplanar orbit scenarios.

摘要

针对异面轨道精确交会问题, 提出了一种基于固体推进的轨道机动方法, 分析了转移时长与脉冲大小之间的关系, 并在脉冲大小固定的前提下, 研究了转移时长与最小交会误差间的关系, 最终将转移轨道设计问题转化为单谷函数极小值点的求解问题, 并设计了一种基于定冲量单脉冲的异面轨道交会控制求解流程。计算目标惯性滑行至虚交点所需时长, 采用Lambert算法求解最小速度增量, 若追踪星脉冲大于该增量, 则结合黄金分割法和最优脉冲制导算法精确求解转移时长和脉冲方向。仿真结果表明, 所提算法具有计算效率高、收敛速度快的特点, 实现了0.6 m的交会精度, 为异面轨道精确交会任务提供了一种有效的解决方案。