基于EPDM热解材料的力学性能研究  

H2 -PID Controller Design for Missile Autopilot Based on Constrained Particle Swarm Optimization

作　　者：张民 应巧萍 

机构地区：南京航空航天大学自动化学院,南京210016

出　　处：《弹箭与制导学报》2016年第1期1-4,9,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金（61174197）资助

摘　　要：为研究固体火箭发动机包覆层材料在不同热解程度下的微观结构和力学行为,通过热重分析得到三元乙丙（EPDM）包覆层的热解温度范围。分别对不同热解温度下的EPDM试件进行力学实验和电镜扫描,并从微观角度分析材料力学行为发生变化的原因。结果表明：在初始热解程度下,材料只是发生了少量的失水和气体的逃逸,其力学行为仍属于粘超弹材料范畴;随着材料热解程度的增加,部分材料基体发生裂解,其力学行为表现为脆性材料特性。Traditional design of missile＇s PID control law only considers robust performances such as amplitude margin, phase margin and so on, which is unable to guarantee multivariate robustness index. In this paper, an easy-to-use method for controller design was presented based on constrained particle swarm optimization （PSO） algorithm. This method takes H robustness index as objective function and auto- matically obtains various parameters. The existing PSO algorithm has been improved by a mapping function, so a constrained optimization problem can be converted into an unconstrained one. Taking the sample missile as the plant, the H-PID controller was designed. Com- nared with nenaltv function algorithm, simulation results show that this method has better performance.

关 键 词：三元乙丙包覆层 热解 单轴拉伸实验 粘超弹材料 脆性材料 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]