航天飞行器在ITAM的AT303高超声速风洞中的空气动力实验研究

摘要

The new wind tunnel AT-303 was commissioned in the Institute of Theoretical and Applied Mechanics in 1999. Owing to the high level of stagnation pressure, AT-303 is able to duplicate realistic flight Reynolds number values of re-entry vehicles, within the Mach number range of 8 to 20. In the frame of an ISTC project conducted by ITAM in collaboration with ESTEC and EADS-ST, aerodynamic investigations of different aerospace vehicles have been performed in the AT-303 wind tunnel. The flow quality and performance of instrumentation of the AT-303 wind tunnel have been checked by testing the HB-2 (AGARD) reference model with force measurements and comparing the results obtained with available experimental and numerical data. Typical aerospace hypersonic vehicles (flight test bed EXPERT supported by ESTEC and potential re-entry demonstrator ARES-H proposed by EADS-ST) have been tested in the Mach and Reynolds number ranges corresponding to realistic flight conditions. Measurements of aerodynamic forces and moments were performed to determine the main aerodynamic characteristics of these vehicles. The paper presents the results of these investigations. An analysis of the experimental data has been conducted, including the comparisons with theoretical data. The lessons learned from these studies are drawn, and recommendations for future studies are proposed.%俄罗斯科学院西伯利亚分院理论与应用力学研究所新研制的AT-303风洞于1999年开始投入使用.由于具有较高的驻点压力,AT-303能够模拟飞行器再入时的真实Reynolds数,其Mach数范围为8～20.在ITAM与ESTEC和EADS-ST协作的ISTC项目的框架下,在AT303风洞中对不同航天飞行器的空气动力特性进行了研究.通过对HB-2(AGARD)参考模型进行测力实验,并将实验结果与其它可用的实验和数值计算结果进行比较,AT-303风洞的流场品质和实验仪器的性能得到了检验.在与实际飞行条件相对应的Mach数和Reynolds数条件下对典型的高超声速航天飞行器进行了实验.测量了气动力和力矩,确定了这些飞行器的主要气动特性.给出了实验结果,对实验数据进行了分析并与理论结果进行了比较.从研究中得到了一些经验,并提出对下一步研究的建议.