摘要
以某型单兵火箭弹为研究对象,进行弹头偏转弹体空气动力效应的风洞实验设计与研究。实验选用低速风洞,在弹头偏转条件下,得到不同位置点在不同偏角和不同攻角的表面压力变化规律。实验使用性价比高的U型管对压力进行实验测量,用不同长度橡胶管对平板压力进行测量,得到U型橡胶管对压力测量的影响关系,对弹头表面所测压力进行修正;从而进一步得出在有攻角的条件下,压力变化受弹体头部偏转影响更明显,并进行相关实验的流体力学数值仿真。为后续的弹头偏转条件下弹体空气动力学数值仿真以及弹道控制研究提供参考数据。
A wind tunnel test was designed to study aerodynamic effects of one personal rocket-assisted projectile （RAP） with deflectable nose. The experimental test was carried out in a low-speed wind tunnel with missile nose deflected, the experiment results shows howthat surface pressure on different points at a point varies with yaw angle and angle of attack. The In the test, measures pressure is measured by using U-tube, which is cost effective. Rubber pipes are used in different lengths to measure pressure distributions of a flat-plate, and the effect of rubber pipe is calculated to modify the measured surface pressure of the nose. Through a set of tests, the analysis of the experiment results showed that with certain angle of attack, nose deflection has a considerable impact on the pressure distribution. Related numerical simulation on fluid dynamics are also carried out. The experiment results can provide reliable raw data for following study on trajectory control and numerical simulation on aerodynamic effects of nose deflection.
出处
《实验室研究与探索》
CAS
北大核心
2014年第4期18-21,25,共5页
Research and Exploration In Laboratory
基金
中国人民解放军总装备部"十二五"预研项目(62201050105)
关键词
空气动力效应
弹头偏转
风洞
aerodynamic effect
deflectable nose
wind tunnel
simulation
