Optimal perturbation guidance with constraints on terminal flight-path angle and angle of attack. (September 2019)

• Record Type: Journal Article
• Authors: Zhao, Penglei; Chen, Wanchun; Yu, Wenbin
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 233:Number 12(2019)
• Page Start: 4436
• Page End: 4446
• Publication Date: 2019-09
• Subjects: Optimal guidance -- flight control -- singular perturbation method -- flight-path angle constraint -- angle of attack constraint; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410018823472
• Languages: English
• ISSNs: 0954-4100

Abstract

This paper presents the design of a singular-perturbation-based optimal guidance with constraints on terminal flight-path angle and angle of attack. By modeling the flight-control system dynamics as a first-order system, the angle of attack is introduced into the performance index as a state variable. To solve the resulting high-order optimal guidance problem analytically, the posed optimal guidance problem is divided into two sub-problems by utilizing the singular perturbation method according to two time scales: range, altitude, and flight-path angle are the slow time-scale variables while the angle of attack is the fast time-scale variable. The outer solutions are the optimal control of the slow-scale subsystem. Thereafter, by applying the stretching transformation, the fast-scale subsystem establishes the relationships between the outer solutions and acceleration command. Then, the optimal command can be obtained by solving the fast-scale subsystem also using the optimal control theory. The proposed guidance can achieve a near-zero terminal acceleration as well as a small miss distance. The superior performance of the guidance is demonstrated by adequate trajectory simulations.