再入环境测量火箭测试平台总体设计与关键技术

目的研究弹头再入飞行时表面的脉动压力等参数特征及变化规律,借助火箭测试平台飞行试验,同步获取自由飞行状态下载荷段外部脉动压力、时均压力、温度与内部结构振动、冲击响应数据,认识和预测脉动压力载荷与结构响应的相关性,同时为结构响应等效的数值模拟验证提供支撑。方法根据飞行试验测试的目的和要求,计算火箭测试平台的总体参数和设计系统组成,开展总体设计技术、测试系统设计技术、防热设计技术、气动弹道设计技术等关键技术研究。结果设计了再入环境测量火箭测试平台,并完成了地面试验验证,用于开展飞行试验,获取典型再入环境下的气动力热数据、弹道参数和结构响应数据。结论通过地面试验,验证了再入环境测量火箭测试平台总体设计的正确性和系列关键技术的有效性。

Overall Design and Key Technologies of the Re-entry Environment Flight Test Rocket

In order to study fluctuating pressure characteristics and laws on the re-entry warhead’s surface,a flight test rocket was designed to obtain fluctuating pressure,average pressure,temperature outside and structural vibration and impact inside of the test section through a free flight,which could help understand and predict the correlation between fluctuating pressure and structural response and provide data to simulate the response of the structure.Under the purpose and requirement of the flight test,the overall parameters and compositions of the rocket were designed and calculated.Several key technologies,such as overall design,test system design,heat shielding,aerodynamic and trajectory design were developed.The re-entry environment flight test rocket was finished,which obtained aerodynamic data,trajectory data and structural response data through flight test successfully.The correction and effectiveness of the flight test rocket’s overall design and key technologies were verification through ground tests.