Modern and future observation Space missions face increasingly more demanding pointing performance requirements. This is accompanied with the development of larger lightweight flexible structures. This paper outlines a methodology for modeling a generic multi-body flexible spacecraft in an end-to-end fashion within the Two-Inputs Two-Outputs Port framework: from disturbance all the way to pointing performance by tacking into account all the uncertainties of each sub-system. A particular focus is dedicated to a novel generic model for Solar Drive Array Mechanisms and its harmonic disturbances produced by the micro-stepping driver and the gearbox imperfections. The proposed model is validated with the on-board telemetries of a European spacecraft. Moreover this paper shows how the proposed model-based approach can be easily used for control design and closed-loop robust performance analysis. Worst-case scenarios of mechanical parameters combination are investigated to provide robust performance certificate of the reference study case. A Linear Parameter-Varying observer, scheduled by the solar array rotor angle, is finally proposed in order to estimate the disturbance torques induced by the gearbox imperfections just using the measurements coming from a classical attitude control system: a star tracker and a gyrometer.

中文翻译：

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太阳能阵列驱动机制引起的微振动的集成建模，用于最坏情况的端到端分析和鲁棒的干扰估计

现代和未来观察太空任务面临着越来越严格的指向性能要求。这伴随着更大的轻质柔性结构的发展。本文概述了一种在“两输入两输出”端口框架内以端到端的方式对通用多体柔性航天器进行建模的方法：从干扰一直到通过考虑每个参数的所有不确定性来指出性能子系统。特别关注的是太阳能驱动阵列机构的新型通用模型及其由微步进驱动器和变速箱缺陷产生的谐波干扰。所提出的模型已通过欧洲航天器的车载遥测技术进行了验证。此外，本文还展示了如何轻松地将所提出的基于模型的方法用于控制设计和闭环鲁棒性能分析。对机械参数组合的最坏情况进行了研究，以提供参考研究案例的可靠性能证明。最终提出了一个由太阳能电池阵列转子角度安排的线性参数变化观测器，以便仅使用来自经典姿态控制系统（恒星跟踪器和陀螺仪）的测量值来估算由齿轮箱缺陷引起的干扰转矩。