利用单向低推力推进系统实现燃料最优编队重构
Fuel-Optimal Formation Reconfiguration by Means of Unidirectional Low-Thrust Propulsion System
AI总结：
本文针对仅配备单个可节流低推力喷管的欠驱动卫星编队，提出一种在制导层安排无推力时段完成姿态重定向、并用类MPC方案闭环控制的燃料最优相对轨道重构方法，以支持LuxSpace的Triton-X任务。
摘要：
使用电推进低推力推进系统进行轨道机动正成为卫星制造商日益青睐的选择，因为这类系统相较于化学推进具有固有优势。许多设计者选择在卫星上安装多个此类推力器以确保全向轨道机动能力，而另一些设计者则选择只为卫星配备单个推力器喷管，以降低轨道控制系统的功率、重量和尺寸需求。本文提出制导与控制方案，以解决由两颗卫星组成的编队的自主最优相对轨道重构问题，其中一颗卫星仅使用单个可节流低推力喷管。这种欠驱动轨道控制系统要求受控航天器持续转动，使喷管指向期望的推力方向。这些重定向姿态机动在制导层内通过安排反复出现的无推力时段加以处理，姿态转动机动即在此时段内进行。随后采用类似模型预测控制（MPC）的方案闭合控制回路。本文的主要动机是为 LuxSpace 旗舰卫星 Triton-X 的未来任务提供支持。由于所提出的制导与控制方案旨在回应现实市场需求，其设计具备若干特定品质，使其从实际应用角度具有吸引力。具体而言，这些方案所需的计算负载极小，并且能够在制导层内容纳运行时间约束，例如在星食期间或地面接触期间不进行推力操作。
英文摘要：
The use of electric low-thrust propulsion systems for orbit maneuvers is becoming a popular choice among satellite manufacturers due to their inherent merits over their chemical counterparts. Many designers choose to incorporate multiple of such thrusters to insure omnidirectional orbit maneuverability, while others choose to equip their satellite with only one thruster nozzle, aiming to reduce the required power, weight, and size of the orbit control system. This paper proposes guidance and control schemes to address the problem of autonomous optimal relative orbit reconfiguration for a formation of two satellites, one of which utilizes a single low-thrust throttleable nozzle. Such under-actuated orbit control system requires the controlled spacecraft to constantly slew to direct the nozzle to the desired thrust direction. These redirection attitude maneuvers are treated within the guidance layer by accommodating recurrent no-thrust periods during which slew maneuvers take place. The control loop is then closed with an MPC-like scheme. The main motivation of this article is to support the future missions of LuxSpace's flagship satellite, Triton-X. Since the proposed guidance and control schemes are meant to answer realistic market needs, they are designed to have some specific qualities that makes them attractive from the practical point of view. Namely, they require minimal computational loads, besides being able to accommodate operational time constraints, e.g. no thrusting during eclipse or during ground contact, within the guidance layer.
机构、总结、中文摘要均由AI分析而来，可能存在错误，请以论文正文为准。
