固液捆绑火箭脉动压力风洞试验与飞行试验对比研究

Comparison of Pressure Fluctuation Wind-Tunnel Test and Flight Test for Solid-Liquid Bundled Launch Vehicles

固液捆绑火箭通常气动外形复杂,跨声速飞行动压大,因此脉动压力抖振载荷严酷。针对某型固液捆绑火箭,为了获取较为准确的跨声速脉动压力特性,在研制阶段开展了脉动压力风洞试验,火箭飞行时也进行了脉动压力测量,以评估飞行状态抖振载荷。采用脉动压力风洞试验和飞行试验进行对比,结果显示,飞行试验各测点脉动压力系数随马赫数变化趋势与风洞试验值一致,峰值大小基本相同,合成功率谱密度函数遥测峰值与设计值相当。研究结果首次验证了固液捆绑火箭跨声速脉动压力设计方法的有效性。

Owing to the complex aerodynamics shape and high flight dynamics pressure,the pressure fluctuation buffet load of solid-liquid bundled launch vehicle is large. In order to achieve more accurate characteristics of the transonic pressure fluctuation,a detailed pulsating pressure wind-tunnel test is carried out in the development stage,and the pressure fluctuation during flight is measured so as to evaluate the buffet load during flight. The comparison of the results obtained from the pulsating pressure wind-tunnel test and the flight test shows that the variation tendency of the pressure fluctuation coefficient of each measured point with the Mach number from the flight test is consistent with that from the wind-tunnel test,and the peak values are almost the same. Besides,the telemetry peak value of the power spectral density is comparable to its design value. These verify the correctness of the design value for the transonic pressure fluctuation of the solid-liquid bundled launch vehicle.