Research on a New Process of Agile Turn with Engine Reignition Based on Optimal Control

Author:

Niu Kang1ORCID,Yu Jianqiao1,Chen Xi1,Yang Di1,Li Ziyuan1

Affiliation:

1. Department of Astronautics, Beijing Institute of Technology, Beijing 100081, China

Abstract

A new process of agile turn with engine reignition is proposed in this paper. Compared with the traditional process, this process includes deceleration phase, larger angle manoeuvre phase, and engine reignition phase. Firstly, the paper describes the new process of agile turn. Then, several constraints in this process are described. Considering all these constraints and assumptions, a new dynamic model including two-stage engine and deceleration parachute is established. Then, the optimal control laws are designed and the timing point determination of the secondary engine ignition is discussed. By using Pontryagin principle, the optimal control laws for each actuator are derived. In terms of determining the optimal timing point of the secondary engine ignition, the paper gives the process of proof. Finally, several numerical simulations are given to demonstrate the effectiveness of the method proposed in this paper. According to all these numerical simulations, it is obvious that the new process of agile turn proposed in this paper is better than traditional process especially in having a smaller turning radius, a shorter turning time, and a high terminal velocity.

Funder

Beijing University of Technology

Publisher

Hindawi Limited

Subject

Multidisciplinary,General Computer Science

Reference35 articles.

1. Neural-adaptive nonlinear autopilot design for an agile anti-air missile;M. Mcfarland

2. An improvement on PWPF modulation of discrete RCS and design of the blended control logic;Y. Lu;Acta Aeronautica et astronautica science,2012

3. Agile turn control considerations for air-to-air missile with reaction jets control system;P. Wang;Journal of Beijing University of Aeronautics and Astronautics,2005

4. Research on the stability of an air-to-air missile lateral thrust and aerodynamic compound control system with a pulse modulator;L. Yan;Navigation Positioning and Timing,2017

5. Finite-time sliding mode attitude control for a reentry vehicle with blended aerodynamic surfaces and a reaction control system;G. Jie;Chinese Journal of Aeronautics,2014

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