机动式再入弹头小滚转气动力风洞试验技术

Experimental technique for micro rolling aerodynamics of a maneuvering reentry body

基于气浮轴承的自由滚转式小滚转力矩测量系统的风洞试验技术,针对传统的惯性再入武器向再入机动武器发展需求,利用多孔光栅及高灵敏度光电传感器测量带小突起(如边条,小配平翼)的非轴对称模型自由滚转状态下的角速度随时间的变化过程。采用理论验证、最小二乘拟合、动力学仿真计算等方法,建立相应滚转力矩气动力模型进行试验数据处理和分析。风洞试验结果显示,数据大小合理,规律性好,同时可获得试验模型在滚转运动中的滚转气动力随时间的变化曲线,以及任意滚转角位置的小滚转静力矩,能够满足机动式再入弹头小滚转气动力测量试验的发展需求。

Micro rolling aerodynamics of a maneuvering reentry body is investigated using wind tunnel test techniques with gas bearing and grating-high sensitivity photoelectric sensor system,so as to meet the continuing developed design requirements of maneuvering reentry vehicles.The measurement system can test the change rules of rotation speed of the asymmetric models,including model with strake and model with trimming wings.According to the change of the rotation speed,the motion equation is rebuilt to simulate the asymmetric model＇s motions,the rolling motion equations are solved using the method of engineering estimation and numerical simulation.The micro rolling aerodynamics can be deducted and analyzed.The time courses of rolling aerodynamics and the static rolling moment at various model attitude can be obtained,and the result obtained shows rational regularity,the requirement of micro-aerodynamic measuring of maneuvering reentry body is satisfied.