TY - GEN
T1 - Three-Dimensional Sliding Mode Guidance Law Based on Variable Universe Fuzzy Control
AU - Zhu, Zejun
AU - Wang, Wei
AU - Ji, Yi
AU - Zhang, Jian
AU - Zhang, Hong Yan
N1 - Publisher Copyright:
© 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
PY - 2023
Y1 - 2023
N2 - This work investigates guidance problem in three-dimensional coordinates with impact angle constraint, speed of system reaching sliding surface and external disturbance, and proposes a fuzzy sliding mode guidance method with time-varying gain parameter adjustment. Specifically, with the segmented sliding mode control, a guidance law which can control the error between the actual impact angle and the desired value to zero, is proposed in this study. This method can solve the slow convergence problem when the sliding mode approaches zero. To speed up the convergence process, some fuzzy rules are formulated by analyzing the interference, and the influence of the error is compensated. Moreover, the variable universe factors are designed to make the parameter variables cover more fuzzy rules. It can be seen from the simulation results, the design of segmented sliding mode can reduce the time that system reaches the sliding surface, the fuzzy sliding mode control can accelerate the convergence rate without affecting the guidance performance. After the introduction of noise, the fuzzy sliding mode control can effectively reduce the interference affect, ensure the stability after sliding mode converges to zero, reduce the overload requirement of the aircraft, and verify the rationality of the designed algorithm.
AB - This work investigates guidance problem in three-dimensional coordinates with impact angle constraint, speed of system reaching sliding surface and external disturbance, and proposes a fuzzy sliding mode guidance method with time-varying gain parameter adjustment. Specifically, with the segmented sliding mode control, a guidance law which can control the error between the actual impact angle and the desired value to zero, is proposed in this study. This method can solve the slow convergence problem when the sliding mode approaches zero. To speed up the convergence process, some fuzzy rules are formulated by analyzing the interference, and the influence of the error is compensated. Moreover, the variable universe factors are designed to make the parameter variables cover more fuzzy rules. It can be seen from the simulation results, the design of segmented sliding mode can reduce the time that system reaches the sliding surface, the fuzzy sliding mode control can accelerate the convergence rate without affecting the guidance performance. After the introduction of noise, the fuzzy sliding mode control can effectively reduce the interference affect, ensure the stability after sliding mode converges to zero, reduce the overload requirement of the aircraft, and verify the rationality of the designed algorithm.
KW - Fuzzy control
KW - Segmented sliding mode
KW - Three-dimensional guidance law
KW - Variable universe factor
UR - http://www.scopus.com/inward/record.url?scp=85151127935&partnerID=8YFLogxK
U2 - 10.1007/978-981-19-6613-2_574
DO - 10.1007/978-981-19-6613-2_574
M3 - Conference contribution
AN - SCOPUS:85151127935
SN - 9789811966125
T3 - Lecture Notes in Electrical Engineering
SP - 5940
EP - 5950
BT - Advances in Guidance, Navigation and Control - Proceedings of 2022 International Conference on Guidance, Navigation and Control
A2 - Yan, Liang
A2 - Duan, Haibin
A2 - Deng, Yimin
A2 - Yan, Liang
PB - Springer Science and Business Media Deutschland GmbH
T2 - International Conference on Guidance, Navigation and Control, ICGNC 2022
Y2 - 5 August 2022 through 7 August 2022
ER -