考虑激光烧蚀不确定性的自适应相对轨道控制
Adaptive Relative Orbit Control Considering Laser Ablation Uncertainty
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中文总结 AI 辅助
本研究针对激光碎片清除任务的相对轨道控制问题，提出结合高斯过程回归的自适应控制方法，通过仿真验证其可抵消激光烧蚀与大气阻力不确定性，提升任务安全性。
中文摘要 AI 辅助
本研究针对激光碎片清除任务，提出一种考虑激光烧蚀与大气阻力不确定性的相对轨道控制律。清除航天器向目标碎片发射激光脉冲，产生用于离轨的烧蚀力；该离轨力会降低目标轨道高度，清除航天器必须跟随目标以保持相对位置，从而实现连续激光照射。问题难点在于激光烧蚀力大小及大气阻力等外部干扰存在不确定性。为解决该问题，本研究推导了一种自适应控制方法，采用高斯过程回归作为非参数回归模型来抵消不确定性。数值仿真在激光烧蚀与大气阻力不确定性条件下验证了所提控制律的有效性。该控制律不仅有助于实现更安全的激光碎片清除任务，还可应用于其他在轨服务任务。
英文摘要
This study proposes a relative orbit control law for laser debris removal missions considering the uncertainties of laser ablation and atmospheric drag. A removal spacecraft irradiates laser pulses to a target debris to generate the ablation force for deorbiting. The deorbiting force lowers the target altitude, and the removal spacecraft must follow it to maintain its relative position for continuous laser irradiation. The difficulty stems from uncertainties of the magnitude of laser ablation and external disturbances such as atmospheric drag. To tackle this problem, this study derives an adaptive control method using the Gaussian process regression to cancel the uncertainties with a nonparametric regression model. Numerical simulations verify the proposed control law under the uncertainties of laser ablation and atmospheric drag. The proposed control law can contribute to the realization of a safer and more secure mission not only for laser debris removal missions, but also for other on-orbit services.
