Purpose

The purpose of this paper is to accomplish robust actuator fault isolation and identification for microsatellite attitude control systems (ACSs) subject to a series of space disturbance torques and gyro drifts.

Design/methodology/approach

For the satellite attitude dynamics with Lipschitz constraint, a multi-objective nonlinear unknown input observer (NUIO) is explored to accomplish robust actuator fault isolation based on a synthesis of H_inf techniques and regional pole assignment technique. Subsequently, a novel disturbance-decoupling learning observer (D²LO) is proposed to identify the isolated actuator fault accurately. Additionally, the design of the NUIO and the D²LO are reformulated into convex optimization problems involving linear matrix inequalities (LMIs), which can be readily solved using standard LMI tools.

Findings

The simulation studies on a microsatellite example are performed to prove the effectiveness and applicability of the proposed robust actuator fault isolation and identification methodologies.

Practical implications

This research includes implications for the enhancement of reliability and safety of on-orbit microsatellites.

Originality/value

This study proposes novel NUIO-based robust fault isolation and D²LO-based robust fault identification methodologies for spacecraft ACSs subject to a series of space disturbance torques and gyro drifts.

中文翻译：

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基于观测器的微卫星姿态控制系统鲁棒执行器故障隔离与识别

目的

本文的目的是为受一系列空间扰动转矩和陀螺漂移影响的微卫星姿态控制系统（ACS）实现鲁棒的执行器故障隔离和识别。

设计/方法/方法

针对具有 Lipschitz 约束的卫星姿态动力学，基于 H _inf技术和区域极点分配技术的综合，探索了多目标非线性未知输入观测器 (NUIO) 来实现稳健的执行器故障隔离。随后，提出了一种新颖的干扰解耦学习观测器（D ² LO）来准确识别孤立的执行器故障。此外，NUIO 和 D ² LO 的设计被重新表述为涉及线性矩阵不等式 (LMI) 的凸优化问题，这些问题可以使用标准 LMI 工具轻松解决。

发现

对微卫星示例进行了仿真研究，以证明所提出的鲁棒执行器故障隔离和识别方法的有效性和适用性。

实际影响

这项研究包括对提高在轨微型卫星的可靠性和安全性的影响。

原创性/价值

本研究提出了基于 NUIO 的鲁棒故障隔离和基于 D ² LO 的鲁棒故障识别方法，适用于受到一系列空间扰动扭矩和陀螺仪漂移影响的航天器 ACS。