文献类型： 外文期刊

作者： Wang, Yujia ¹ ; Dong, Jinlu ³ ; Wang, Muyuan ⁴ ; Wu, Wenqi ⁶ ;

作者机构： 1.Chinese Acad Trop Agr Sci, Inst Agr Machinery Res, Guangzhou 524091, Guangdong, Peoples R China

2.Natl Univ Singapore, Dept Chem & Biomol Engn, Singapore 117585, Singapore

3.Shandong Jiaotong Univ, Sch Informat Sci & Elect Engn, Sch Artificial Intelligence, Jinan, Shandong, Peoples R China

4.Chinese Acad Sci, Changchun Inst Opt Fine Mech & Phys, Changchun 130033, Peoples R China

5.Chinese Acad Sci, Beijing 10049, Peoples R China

6.Hong Kong Polytech Univ, Dept Ind & Syst Engn, Hung Hom, Hong Kong, Peoples R China

关键词： Actuator faults; Mismatched disturbances; Observer-free; Fault-tolerant control

期刊名称：AEROSPACE SCIENCE AND TECHNOLOGY （ 影响因子：5.8； 五年影响因子：5.6 ）

ISSN： 1270-9638

年卷期： 2025 年 165 卷

页码：

收录情况： SCI

摘要： This paper presents an innovative observer-free sliding mode control strategy to address the challenging tracking control problem of near-space hypersonic vehicles with unknown actuator faults, mismatched disturbances, and matched disturbances. Unlike traditional fault-tolerant control methods, this approach eliminates the need for observers and precise information about faults and disturbances, simplifying implementation while ensuring robust performance. The study begins by constructing a rigid-body dynamics model for near-space hypersonic vehicles. By introducing indirect variables, the under-actuated system is transformed into a fully actuated one, enabling tracking control design. Subsequently, a novel sliding mode surface is proposed, followed by the design of a sliding mode controller to achieve reliable tracking performance in the presence of uncertainties and actuator faults. Numerical simulations validate the effectiveness of the proposed method by comparing it with stateof-the-art methods, such as fixed sliding mode control, logarithmic sliding mode control, and fractional-order sliding mode control, demonstrating performance improvements, with reductions in integral of squared error, integral of absolute error, and time-weighted integral of absolute error ranging from 7.55% to 97.99%, even under mismatched disturbances and actuator faults. These results show its potential for improving fault-tolerant control of near-space hypersonic vehicles.