再入飞行力热环境测量的模型飞行试验设计

目的获取钝锥外形飞行器再入飞行力热环境参数,建立更为准确的环境预测模型,开展基于无控火箭的模型飞行试验设计。方法根据转捩区、湍流区时间提出了无控惯性飞行弹道的落速约束。根据环境预测建模需要,确定环境参数类型及测点布局。采用弹道耦合的气动加热计算模型、脉动压力预示的工程算法、脉动压力与发动机激励下振动响应的相似外推方法等计算分析飞行全程的内外温度、时均压力、脉动压力和振动环境。结果得到了温度、压力和振动环境的极值,确定了主要测量技术要求。结论外部温度量程范围为0~400℃,可测量的最大温度变化率不低于20℃/s。压阻式传感器量程上限为25PSI,压电式传感器量程上限为5 PSI,耐高温环境不低于220℃且具有温度补偿功能。振动量程范围为–100g~+100g。

Model Flight Test Design to Measure Re-entry Aero-thermal-dynamic Environments

To collect aero-thermal-dynamic environments of a blunt conical re-entry body and establish the environmental prediction method,a model flight test based on uncontrolled rocket was designed.The impact velocity was determined by transition and turbulent lasting time.The environmental parameters and sensor locations were discussed..According to the nominal trajectory,several predicting methods were employed to get the exterior and interior temperature,static and fluctuate pressure,vibration environments during the flight,including trajectory coupled aerothermodynamics computing model,empirical formula of fluctuate pressure,vibration extrapolation based on similar vehicle.The maximum temperature,pressure and vibration were computed,and major specifications were defined.The exterior air temperature ranges 0~400℃,and the maximum rate is up to 20℃/s.The piezo-resistive pressure sensor ranges up to 25 PSI,and the piezo-electric pressure sensor ranges up to 5 PSI.Pressure sensors work under 220℃with temperature compensation.The vibration acceleration ranges–100g~+100g.