A novel fractional order PID navigation guidance law by finite time stability approach. (November 2019)

• Record Type: Journal Article
• Authors: Pan, Binfeng; Fareed, Usman; Qing, Wenjie; Tian, Shaohua
• Is Part Of: ISA transactions. Volume 94(2019)
• Page Start: 80
• Page End: 92
• Publication Date: 2019-11
• Subjects: Fractional order PID guidance -- 6 degrees-of-freedom model -- Finite time stability -- Circle criterion -- Maneuvering targets; Engineering instruments -- Periodicals; Engineering instruments; Periodicals; Electronic journals; 629.805
• DOI: 10.1016/j.isatra.2019.04.019
• Languages: English
• ISSNs: 0019-0578

Abstract

Abstract: In this paper, a novel fractional order proportional–integral–differential navigation guidance law utilizing finite time stability approach is presented in order to achieve robust performance for intercepting incoming targets. The proposed guidance law is designed following three-loop guidance and control scheme, considering the interceptor's nonlinear 6 degrees-of-freedom model. In the outer loop, normal acceleration commands are generated by the proposed guidance law. In the intermediate loop, these commands are converted into equivalent body rate commands, which are tracked by dynamic inversion based autopilot in the inner loop. A fractional order circle criterion is developed for the finite time stability analysis of this proposed guidance law, whose stability conditions give an analytical bound for the flight up time in which stability can be insured. Extensive 6 degrees-of-freedom simulations and a variety of comparison studies against maneuvering targets are implemented to demonstrate the effectiveness of the proposed guidance law. The simulation results show that the proposed guidance law has better performance when comparing with the proportional navigation and proportional–integral–differential navigation guidance laws. Highlights: A novel FO-PIDNG law utilizing finite time stability approach is presented. A fractional order circle criterion for finite time stability analysis is developed. A 6-DoF missile model with 3 loop guidance and control scheme is considered. Advantage of the proposed law is compared with PNG and PIDNG laws.