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首页> 外文期刊>Aerospace science and technology >Tube-based robust model predictive control for spacecraft proximity operations in the presence of persistent disturbance
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Tube-based robust model predictive control for spacecraft proximity operations in the presence of persistent disturbance

机译：存在持续扰动的航天器接近操作的基于管的鲁棒模型预测控制

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摘要

Rendezvous and Proximity Operations (RPOs) of two autonomous spacecraft have been extensively studied in the past years, taking into account both the strict requirements in terms of spacecraft dynamics variations and the limitations due to the actuation system. In this paper, two different Model Predictive Control (MPC) schemes have been considered to control the spacecraft during the final phase of the rendezvous maneuver in order to ensure mission constraints satisfaction for any modeled disturbance affecting the system. Classical MPC suitably balances stability and computational effort required for online implementation whereas Tube-based Robust MPC represents an appealing strategy to handle disturbances while ensuring robustness. For the robust scheme, the computational effort reduction is ensured adopting a time-varying control law where the feedback gain matrix is evaluated offline, applying a Linear Matrix Inequality approach to the state feedback stabilization criterion. An extensive verification campaign for the performance evaluation and comparison in terms of constraint satisfaction, fuel consumption and computational cost, i.e. CPU time, has been carried out on both a three degrees-of-freedom (DoF) orbital simulator and an experimental testbed composed by two Floating Spacecraft Simulators reproducing a quasi-frictionless motion. Main conclusions are drawn with respect to the mission expectations. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：过去几年中，考虑到航天器动力学变化方面的严格要求以及驱动系统的局限性，已经对两架自动航天器的交会和近距操作（RPO）进行了广泛的研究。在本文中，已经考虑了两种不同的模型预测控制（MPC）方案来在交会机动的最后阶段控制航天器，以确保对影响系统的任何模型扰动都能满足任务约束条件。经典MPC适当地平衡了在线实现所需的稳定性和计算工作量，而基于Tube的鲁棒MPC则是一种在确保鲁棒性的同时处理干扰的有吸引力的策略。对于鲁棒方案，采用时变控制定律来确保计算量减少，在该定律下，离线评估反馈增益矩阵，并对状态反馈稳定准则应用线性矩阵不等式方法。已在三自由度（DoF）轨道模拟器和由以下人员组成的实验测试台上进行了广泛的验证活动：性能评估和比较约束满足，燃料消耗和计算成本（即CPU时间）两个漂浮的航天器模拟器，可再现准无摩擦运动。得出与任务期望有关的主要结论。 （C）2018 Elsevier Masson SAS。版权所有。

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  • 来源
    《Aerospace science and technology》 |2018年第6期|585-594|共10页
  • 作者

    Mammarella M.; Capello E.; Park H.; Guglieri G.; Romano M.;

  • 作者单位

    Politecn Torino, Dept Mech & Aerosp Engn, Corso Duca Abruzzi 24, I-10129 Turin, Italy;

    Politecn Torino, CNR, IEIIT, Dept Mech & Aerosp Engn, Corso Duca Abruzzi 24, I-10129 Turin, Italy;

    New Mexico State Univ, Dept Mech & Aerosp Engn, Las Cruces, NM 88003 USA;

    Politecn Torino, Dept Mech & Aerosp Engn, Corso Duca Abruzzi 24, I-10129 Turin, Italy;

    US Navy, Postgrad Sch, Dept Mech & Aerosp Engn, 1 Univ Circle, Monterey, CA 93943 USA;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Robust control; Model predictive control; Automated rendezvous and docking;

    机译：鲁棒控制;模型预测控制;自动会合和对接;

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