用三种滤波器实现卫星姿态容错估计，提升在轨可靠性。
Fault-Tolerant Spacecraft Attitude Determination using State Estimation Techniques
- 采用扩展/无迹/粒子滤波器构建容错姿态估计算法。
- 在低地球轨道大型卫星上验证了不同故障模式下的滤波性能。
- 适合航天器自主导航与故障处理系统研究者参考。
扩展卡尔曼滤波器、无迹卡尔曼滤波器和粒子滤波器为航天器的姿态容错估计提供了稳健框架。本文研究了这些滤波器在低地球轨道大型卫星上的表现，并分析了基于它们的多种故障检测、隔离与恢复技术。关键结果包括在不同故障模式下各滤波器的性能表现。
原文摘要 · Abstract (English)
The extended and unscented Kalman filter, and the particle filter provide a robust framework for fault-tolerant attitude estimation on spacecraft. This paper explores how each filter performs for a large satellite in a low earth orbit. Additionally, various techniques, built on these filters, for fault detection, isolation and recovery from erroneous sensor measurements, are analyzed. Key results from this analysis include filter performance for various fault modes.
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