一种多星分离的姿控联合仿真方法

A Joint Simulation Method for Multi-Satellite Separation with Attitude Control

现阶段仅依据多体动力学,难以准确分析和评估多星分离时含调姿过程的近远场分离过程。因此针对一箭多星任务的分离安全性设计需求,提出了一种姿控联合仿真方法,实现了近远场分离的实时调姿仿真。计算结果表明,该方法与专业弹道软件相比,计算误差不超过5%。同时为了进一步研究结构参数、动力学参数和调姿算法等变量对分离方案的影响,结合拉丁超立方采样和蒙特卡罗打靶法,优化了采样空间,从而可以快速分析变量偏差、采样方式对不同分离工况的影响,进而准确判定分离方案的安全性。该方法实现了参数的自动化设置,可有效提高仿真效率,能为一箭多星发射任务的快速论证及分离安全性设计需求提供有力支撑。

Currently,accurately analyzing and evaluating the separation process of multiple stars,particularly during near-far field separation with attitude adjustments,poses challenges when relying solely on multi-body dynamics.To address the safety design requirements for a multi-satellite mission's separation,a combined attitude control simulation method is proposed,real-time attitude adjustment simulations during near-far field separation are achieved.The computed results demonstrate that,compared to specialized ballistic software,the computational error of this method does not exceed 5%.Furthermore,to investigate the influence of variables such as structural parameters,dynamic parameters,and attitude adjustment algorithms on the separation scheme,a combination of Latin hypercube sampling and the Monte Carlo shooting method is utilized to optimize the sampling space.This allows for a swift analysis of variable deviations and the impact of sampling methods on different separation conditions,enabling an accurate assessment of the separation scheme's safety.This method automates parameter settings,improves simulation efficiency,and provides robust support for the rapid validation and safety design requirements of a multi-satellite launch mission.