旋转导弹风洞动态测力试验技术研究  

Research on test technology of dynamic force measurement of rotating missile in wind tunnel

作　　者：董金刚[1] 金佳林 李广良[1] 秦永明[1] 马汉东[1] DONG Jingang;JIN Jialin;LI Guangliang;QIN Yongming;MA Handong(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2020年第4期81-86,共6页Journal of Experiments in Fluid Mechanics

摘　　要：常规风洞静态气动力测量技术无法得到旋转导弹的非定常气动特性数据,需要研究在风洞中模拟旋转导弹运动特征以及对气动力实现动态测量的试验技术。在1.2m量级超声速风洞中,研究了大长细比导弹模型旋转运动主动控制技术以及与旋转运动对应的动态测量试验技术。采用旋转导弹模型(长细比为20)对建立的试验技术进行了风洞试验验证。结果表明:采用微型驱动系统并对旋转组件与导弹模型进行一体化设计,可以对大长细比导弹模型转速进行稳定控制;建立的风洞动态测力试验技术可以对导弹模型旋转运动下的动态数据进行测量,试验数据重复性精度良好。The missile encounters complex aerodynamic problems during the rotating flight.The rotary motion causes unsteady aerodynamic characteristics.The conventional static force measurement wind tunnel test cannot meet the requirements of the dynamic aerodynamic characteristics research,and the dynamic aerodynamics of missile model needs to be measured in the wind tunnel,the rotational motion of missile model performs similar simulations.In the 1.2 m-level supersonic wind tunnel,the active control technology of the rotary motion of the long slender missile model and the dynamic aerodynamic measurement technology corresponding to the rotary motion are studied.The established test technique was verified by the wind tunnel test using a rotating missile model with a slenderness ratio of 20.The experimental results show that the micro-drive system and the integrated design of the rotating component and the missile model can stably control the rotational speed of the missile model with large slenderness ratio.The established wind tunnel dynamic force test technology can obtain the dynamical data of the missile model in rotating motion,and the test data was reproducible with good precision.

关 键 词：旋转导弹 风洞试验 非定常气动力 动态试验技术 旋转运动 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]