Nonlinear Earth orbit control using low-thrust propulsion
Nonlinear Earth orbit control using low-thrust propulsion
复制标题
使用低推力推进的非线性地球轨道控制
DOI：
10.1016/j.actaastro.2020.10.037
复制
发表时间：
2021
影响因子：
3.5
通讯作者：
M. Pustorino
中科院分区：
文献类型：
--
作者：
M. Pontani;M. Pustorino
这项研究的重点是定义、分析和数值测试一种有效的非线性轨道控制技术，用于补偿轨道摄动以及中低空地球轨道卫星轨道注入时可能出现的误差。提出了一种通用的、系统的实时轨道控制方法，假设目标卫星配备了一个可操纵和可节流的小推力推进系统。考虑了两种不同的运行轨道：(A)极低高度地球轨道和(B)中等高度地球轨道。提出了一种基于Lyapunov稳定性理论的反馈控制律，并对其进行了验证。解析地建立了一些显着的稳定性性质。然后，研究了(A)和(B)两种情况下的非线性控制在5年内的总体性能。还考虑了卫星食对可用电能的影响。对于任务情景(A)，对所需(名义)条件的适当容差可大大节省推进剂需求。
This research is focused on the definition, analysis, and numerical testing of an effective nonlinear orbit control technique tailored to compensating orbit perturbations, as well as possible errors at orbit injection of low- and medium-altitude Earth-orbit satellites. A general, systematic approach to real-time orbit control is presented, under the assumption that the satellite of interest is equipped with a steerable and throttleable low-thrust propulsion system. Two different operational orbits are considered: (a) very-low-altitude Earth orbit and (b) medium-altitude Earth orbit. A feedback control law based on Lyapunov stability theory is proposed and tested. Some remarkable stability properties are established analytically. Then, the overall performance of the nonlinear control at hand is investigated for cases (a) and (b), over 5 years. The effect of satellite eclipsing on available electrical power is considered as well. For mission scenario (a), suitable tolerances on the desired (nominal) conditions allow substantial savings in terms of propellant requirements.
影响因子：
2.6
作者：
C. Kluever
通讯作者：
C. Kluever