激光烧蚀离轨非合作卫星的编队保持控制
Formation Keeping Control for Deorbiting an Uncooperative Satellite by Laser Ablation
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中文总结 AI 辅助
本文提出一种基于解析解的编队保持控制律，通过激光烧蚀和电推力时机与方向控制，使追踪器与目标同时离轨并周期回归期望编队，经数值模拟和蒙特卡洛验证有效。
中文摘要 AI 辅助
本文提出了利用激光烧蚀使碎片离轨的编队保持控制律。激光烧蚀是接触式主动碎片清除的关键技术，其中携带激光系统的追踪卫星向目标物体发射激光脉冲，以产生用于离轨的烧蚀力。离轨力使目标减速，追踪器必须保持其相对位置并继续照射。换言之，追踪器和目标都应同时离轨，两者都有加速度。尽管传统的编队飞行任务假设只有追踪器进行机动，但本文中的编队飞行考虑了追踪器和目标都具有加速度的情况。因此，本文推导了动力飞行中追踪器与目标之间的相对运动方程及其利用相对轨道要素的解析解。提出了一种基于解析解的控制律，该控制律确定激光烧蚀和电推力的时机和方向，使编队周期性地返回期望编队。数值模拟首先在两种不同机动时机的情况下检验了控制律。然后，进行蒙特卡罗模拟，以验证该控制律对各种期望编队的有效性。
英文摘要
This paper proposes the formation keeping control law for deorbiting debris by a laser ablation. Laser ablation is vital technology for contactless active debris removal, where a chaser satellite with a laser system irradiates laser pulses to a target object to generate the ablation force for deorbiting. The deorbiting force decelerates the target, and the chaser must maintain its relative position and continue irradiating. In other words, both the chaser and the target are supposed to be deorbited simultaneously, where both have accelerations. Although conventional formation flying missions assume that only a chaser maneuvers, the formation flying in this paper considers that both a chaser and a target have accelerations. Thus, this paper derives the relative equations of motion between the chaser and the target in powered flight and their analytical solution using relative orbital elements. A control law based on the analytical solution is proposed, which determines the timings and directions of the laser ablation and the electrical thrust so that the formation periodically returns to a desired formation. Numerical simulations first examine the control law in two cases with different maneuver timings. Then, a Monte Carlo simulation is performed to verify the effectiveness of the control law for a variety of desired formations.
发表机构
- Kyushu University（九州大学）
- SKY Perfect JSAT Corporation（SKY完美JSAT公司）
机构由 AI 辅助整理，请以论文原文为准。
