内埋武器高速风洞弹射投放模型试验关键技术研究

针对新一代战斗机超声速内埋武器弹射投放分离安全性问题,采用高速风洞投放实验技术研究内埋武器从开式武器舱弹射投放分离动态运动过程,风洞投放模型试验过程中采用除垂直加速度不足外,其余全部运动严格相似的轻模型相似设计方法,并针对轻模型法垂直加速度不足所导致的投放垂直位移偏离实物位移问题,采用一种简单易行的公式修正法进行补偿,试验给出了不同初始弹射投放分离条件下,内埋武器从载机投放分离后运动轨迹与姿态角随分离时间的变化规律,试验马赫数$Ma = 1.5$.研究结果表明:初始投放分离角速度对内埋武器投放分离后的运动轨迹及姿态角有较大的影响,当初始投放分离角速度$\omega _{z0}^s = 0^\circ/{\rm s}$时,内埋导弹出舱后先向下运动远离载机的流场干扰区,之后逐渐向载机方向抬升靠近并最终碰撞载机,高速风洞投放试验结果是不安全的,但经过公式修正后投放试验结果比较乐观,垂直方向运动仍然一直下降远离载机,这说明采用高速风洞投放试验得出的导弹不安全投放分离对真实载机来说不一定会出现,高速风洞投放试验结果比较保守. 当初始投放分离角速度$\omega _{z0}^s= 15^\circ/{\rm s}$和$\omega _{z0}^s = 30^\circ/{\rm s}$时,内埋导弹投放分离后运动趋势几乎一致, 均没出现向载机靠近的现象,内埋导弹具有一定的初始投放分离角速度有利于内埋武器的安全分离. 

THE CRUCIAL TECHNIQUE INVESTIGATION OF WIND-TUNNEL DROP-MODEL TESTING FOR THE SUPERSONIC INTERNAL WEAPONS

A wind tunnel drop-model testing technique is applied to study the dynamic separational process for the internal weapon from the open weapon cabin ejection for the separation safety problem of supersonic internal weapon ejection delivery, The light model similar design method is used in the wind tunnel drop-model testing which all movement is strictly comparable in addition to lack of vertical acceleration and the lack of the vertical acceleration can cause displacement deviation real displacement. in the end we use a simple formula method to compensation the lacking vertical displacement. the experiment gives the law of separation trajectory and attitude for the different initial ejection separation condition, the test Mach number is $Ma= 1.5$. The results show that the initial separation angle velocity has a great influence on the motion trajectory and the attitude angle for the internal weapon. When the initial separation angle speed is $\omega _{z0}^s = 0^\circ/{\rm s}$, the internal missile firstly moves down to the disturbed flow field far from the cariier the separation,then it gradually moves towards to the carrier direction and collides the carried vehicle. The experimental results of high speed wind tunnel are unsafe,but the result is optimistic after the formula is corrected. This shows that the unsafe separation of missiles obtained by the high speed wind tunnel test may not necessarily occur for the aircraft and the results that obtained by the high speed wind tunnel test are conservative. When the initial separation angle speed is $\omega _{z0}^s = 15^\circ/{\rm s}$, $\omega _{z0}^s = 30^\circ/{\rm s}$, the movement trend of the embedded missile is almost the same and there is no approaching the carrier aircraft. The embedded missile which has a certain initial delivery angle is conducive to the safe separation of internal weapons.