In order to improve the safety and reliability of the hypersonic flight vehicle, a sliding mode observer-based fault detection scheme is applied in this paper to handle the actuator fault detection issue, including stuck fault detection and PLOE fault detection. A dynamic linear model with uncertainty is first derived from the original nonlinear hypersonic flight vehicle model by using Taylor’s linearization approach at the equilibrium point. Secondly, the actuator fault model, reflecting stuck faults and PLOE faults, is constructed. Then, a sliding mode-based fault detection observer, considering system decomposition, is developed based on the linearized hypersonic flight vehicle model. At last, the designed sliding mode observer is applied to the original nonlinear hypersonic flight vehicle for single-input, single-style actuator fault detection. The simulation results show that stuck faults and big proportion PLOE faults can be timely and accurately detected at the fault time, and the stuck actuator fault from input 3 can cause a deadly impact to the hypersonic flight vehicle, which deserves much more attention than the actuator faults from the other three inputs. Meanwhile, the detection of a small proportion of PLOE faults encounters some difficulties and needs special attention and further investigation.

中文翻译：

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基于滑模观测器的高超声速飞行器卡滞故障和部分失效（PLOE）故障检测

为了提高高超声速飞行器的安全性和可靠性，本文采用基于滑模观测器的故障检测方案来处理执行器故障检测问题，包括卡住故障检测和PLOE故障检测。首先利用平衡点处的泰勒线性化方法，从原始非线性高超声速飞行器模型中推导出具有不确定性的动态线性模型。其次，构建了反映卡住故障和PLOE故障的执行器故障模型。然后，基于线性化高超声速飞行器模型，开发了一种考虑系统分解的基于滑模的故障检测观测器。最后，将设计的滑模观测器应用于原非线性高超声速飞行器，进行单输入、单式执行器故障检测。仿真结果表明，卡死故障和大比例PLOE故障可以在故障时刻及时准确地检测到，输入3的执行器卡死故障会对高超声速飞行器造成致命影响，比执行器更值得关注。其他三个输入的故障。同时，小部分PLOE故障的检测遇到了一些困难，需要特别注意和进一步调查。