Modeling and Simulation of Aircraft Guidance with Over-gravity Compensation
作者单位：Xi'an Research Institution of High-Tech Science and Technology on Electro-optic Control Laboratory
会议名称：《第36届中国控制会议》
会议届次：36
主办单位：Dalian University of Technology;Systems Engineering Society of China (SESC);Technical Committee on Control Theory (TCCT), Chinese Association of Automation (CAA)
会议日期：2017年
学科分类：08[工学] 081105[工学-导航、制导与控制] 0804[工学-仪器科学与技术] 0811[工学-控制科学与工程]
基 金：supported by National Natural Science Foundation of China under grant 61304239 and 61673386 Aviation Foundation of China under grant 201651U8006
关 键 词：over-gravity compensation three-dimensional simulation falling angle miss distance
摘 要：In order to improve the attack effect from the top of maneuver target for air-to-ground missile,three-dimensional proportional navigation model with over-gravity compensation is established based on the relative motion ***-dimensional ballistic trajectory of the missile attacking target is simulated based on the guidance and control closed-loop *** effect of the over-gravity compensation proportional navigation parameters on the flight characteristics is *** simulation results indicate the effectiveness of the proposed navigation *** addition,the theoretical analysis results are also verified.