防空导弹雷达导引头性能指标对目标拦截的仿真分析
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摘要
以采用直线运动或蛇形机动的反舰弹为目标,对防空导弹的拦截进行建模与仿真,分析防空导弹零偏,隔离度,视线角速度测量噪声,天线罩斜率等导引头性能指标对拦截弹命中概率的影响。首先对各性能指标进行单因素分析,给出了允许脱靶量和命中概率指标下各导引头参数的取值范围;然后在此基础上对各因素进行水平划分,采用正交试验法进行了试验设计,多因素综合仿真分析表明各性能指标之间具有相互制约关系。
Aiming at the linear or weaving maneuvering anti-ship missile,the interception modeling and simulation of air defense missile is carried out. The influence of seeker performance indexes such as zerooffset,disturbance rejection rate,line-of-sight angular velocity measurement noise,radome slope on the kill probability of interceptor are analyzed. Firstly,the single factor analysis of each performance index is carried out,and the range of parameters of each seeker performance indexes under the allowable miss distance and kill probability index are given. Then,the factors are divided into various levels,and the experiment design is carried out by using the orthogonal test method. The experimental design and multifactor comprehensive simulation analysis show that each performance index has a mutual constraint relationship.
Aiming at the linear or weaving maneuvering anti-ship missile,the interception modeling and simulation of air defense missile is carried out. The influence of seeker performance indexes such as zerooffset,disturbance rejection rate,line-of-sight angular velocity measurement noise,radome slope on the kill probability of interceptor are analyzed. Firstly,the single factor analysis of each performance index is carried out,and the range of parameters of each seeker performance indexes under the allowable miss distance and kill probability index are given. Then,the factors are divided into various levels,and the experiment design is carried out by using the orthogonal test method. The experimental design and multifactor comprehensive simulation analysis show that each performance index has a mutual constraint relationship.
引文
[1]迟刚,王树宗.便携式防空导弹拦截巡航导弹效能仿真研究[J].系统工程与电子技术,2004,26(2):261-263.
[2]杜运理,夏群力,蔡春涛.雷达导引头天线罩误差对制导精度影响研究[J].弹箭与制导学报,2010,30(5):79-82.
[3] Nesline F,Zarchan P. Radome induced miss distance in aerodynamically controlled homing missiles[C]. Fluid Dynamics,Plasma Dynamics, and Lasers Conference,2013.
[4]李富贵,夏群利,蔡春涛,等.导引头隔离度对寄生回路稳定性的影响[J].红外与激光工程,2013,42(9):2341-2347.
[5]郑多,林德福,徐兴华,等.天线罩和导引头隔离度对制导系统影响研究[J].系统工程与电子技术,2015,37(7):1596-1603.
[6]田宏亮,梁晓庚,贾晓洪,等.视线角速度测量干扰对制导系统的影响[J].弹道学报,2012,24(3):65-69.
[7]周慧钟.有翼导弹飞行动力学[M].北京:北京航空航天大学出版社,1983:78-83
[8] Zarchan P. Tactical and strategic missile guidance,sixth edition[J]. American Institute of Aeronautics&Astronautics Inc,1994,(6):555.
[9]魏毅寅.世界导弹大全[M].北京:军事科学出版社,2011.
[10]夏伯忠.正交试验法[M].长春:吉林人民出版社,1985.
[2]杜运理,夏群力,蔡春涛.雷达导引头天线罩误差对制导精度影响研究[J].弹箭与制导学报,2010,30(5):79-82.
[3] Nesline F,Zarchan P. Radome induced miss distance in aerodynamically controlled homing missiles[C]. Fluid Dynamics,Plasma Dynamics, and Lasers Conference,2013.
[4]李富贵,夏群利,蔡春涛,等.导引头隔离度对寄生回路稳定性的影响[J].红外与激光工程,2013,42(9):2341-2347.
[5]郑多,林德福,徐兴华,等.天线罩和导引头隔离度对制导系统影响研究[J].系统工程与电子技术,2015,37(7):1596-1603.
[6]田宏亮,梁晓庚,贾晓洪,等.视线角速度测量干扰对制导系统的影响[J].弹道学报,2012,24(3):65-69.
[7]周慧钟.有翼导弹飞行动力学[M].北京:北京航空航天大学出版社,1983:78-83
[8] Zarchan P. Tactical and strategic missile guidance,sixth edition[J]. American Institute of Aeronautics&Astronautics Inc,1994,(6):555.
[9]魏毅寅.世界导弹大全[M].北京:军事科学出版社,2011.
[10]夏伯忠.正交试验法[M].长春:吉林人民出版社,1985.