升力体飞行器尾喷流模拟气动力试验方法研究

发布时间：2018-05-10 05:44

  本文选题：吸气式飞行器 + 升力体　； 参考：《空气动力学学报》2016年01期

【摘要】：尾喷流对升力体高超声速飞行器的气动特性影响显著,风洞喷流模拟测力试验是研究升力体飞行器尾喷流干扰效应的重要手段。在尾喷流模拟气动力试验中,选取恰当的喷流模拟参数,以及克服喷流供气管路对天平测力的干扰以提高测量精准度,是需要解决的关键技术。在CARDC的Ф1米高超声速风洞中,研究了采用冷喷流模拟、飞行器整体模型测力的升力体飞行器尾喷流模拟测力试验方法。通过优化模型结构设计、选用小干扰的喷管分断缝隙密封措施,解决了带尾喷流模拟条件下的升力体飞行器气动力精确测量问题,提高了带喷流气动力试验数据精度,接近常规气动力试验的水平。
[Abstract]:The effect of tail jet on aerodynamic characteristics of lift hypersonic vehicle is significant. Wind tunnel simulation test of jet force measurement is an important means to study the effect of tail jet interference on lift body vehicle. In the aerodynamic test of tail jet simulation, the key technology to be solved is to select appropriate parameters of jet simulation, and to overcome the interference of jet supply line to the balance force measurement to improve the accuracy of measurement. In a 1 meter hypersonic wind tunnel of CARDC, a method for simulating the force measurement of the tail jet of a lift vehicle by using a cold jet simulation and a global model of the vehicle is studied. By optimizing the structural design of the model and selecting the small interference nozzle break slot sealing measures, the precise measurement of the aerodynamic force of the lift vehicle under the condition of simulation with tail jet flow is solved, and the accuracy of the aerodynamic test data with the jet flow is improved. Close to the level of conventional aerodynamic tests.
【作者单位】： 中国空气动力研究与发展中心超高速空气动力研究所;中国空气动力研究与发展中心高超声速冲压发动机技术国防科技重点实验室;
【分类号】：V211.7
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本文编号：1868017