发射环境下导弹折叠翼的展开试验及仿真分析  

Test and Simulation of Deployment Process of Missile Folding-wings during Launching

作　　者：甄文强 杨奇[1] 姬永强[1] 石运国[1] ZHEN Wen-qiang;YANG Qi;JI Yong-qiang;SHI Yun-guo(Institute of Systems Engineering,China Academy of Engineering Physics,Mianyang 621999,Sichuan,China)

机构地区：[1]中国工程物理研究院总体工程研究所,四川绵阳621999

出　　处：《兵工学报》2018年第9期1756-1761,共6页Acta Armamentarii

基　　金：中国工程物理研究院总体工程研究所科技专项基金项目(2017KJZ01)

摘　　要：对导弹折叠翼在发射环境下的展开过程进行研究,通过小型试验弹模拟真实发射环境,对两种不同刚度的折叠翼进行试验,获取了折叠翼展开过程的图像资料和弹道数据。考虑试验弹发射过程扰动带来的攻角变化,建立包含试验弹速度和攻角的折叠翼展开过程动力学模型,分析了攻角对折叠翼展开过程的影响,并与计算流体力学方法进行对比分析,得出了在翼面转动角度较大时一致性较好的结论。试验中出现了小刚度折叠翼展开不同步现象,其中下侧迎风翼面明显滞后,在动力学模型中引入试验实测的弹体速度和攻角,分析得到的结果与试验结果较为吻合,表明了该模型的正确性。The deployment process of missile folding-wing during launching is studied.The real launching processes of test missiles are simulated,two kinds of folding-wings with different stiffness are tested,and some images and trajectory data of the test missiles are obtained.A dynamic model of deployment process of folding-wings,including the angle of attack and the velocity of test missile,is established,in which the change in angle of attack of test missile is due to launching disturbance.The comparison of the proposed dynamic model and CFD method shows a good agreement for the large rotating angle of airfoil surface.In the test,the deployments of the little stiffness folding-wings are unsynchronized,the deployments of the lower wings are lagged obviously.The proposed dynamic model gives the results of the deployment process by using the measured velocity and angle of attack.

关 键 词：导弹折叠翼 展开试验 发射环境 动力学仿真 攻角 

分 类 号：TJ760.13[兵器科学与技术—武器系统与运用工程]