高超声速飞行器表面测热技术综述

doi:10.7527/S1000-6893.2013.0401

Abstract

Abstract:

The aero thermal heating rate of hypersonic vehicle surfaces is a key input parameter for thermal protection system design, It is of great significance, in view of the limitation of computation and ground test, to obtain the aerothermal heating rate in the real environment of flight, and then validate and upgrade the computation code and ground test based on this information. Typical flight missions in the world and their in-flight heat transfer measurement plans since the 1950s are enumerated in this study. With the "Design in" and "Add on" as the classification features for heat measuring technology, various instruments and corresponding flight results are described. The impact of "thermal matching" and "structural matching" is analysed as a key factor for the flight heat transfer measurement technology, solution of the problem and engineering experience introduced by flight test examples. A conclusion is made for the general and specific characteristics, and the development trend for heat measurement technology. Finally, suggestions are made based on the above study for future research in this field.

Key words: hypersonic vehicle, surface heat flux, flight test, heat flux measurement, thermal matching

CLC Number:

V417
V441

MENG Songhe, DING Xiaoheng, YI Fajun, ZHU Yanwei, XIE Weihua. Overview of Heat Measurement Technology for Hypersonic Vehicle Surfaces[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(7): 1759-1775.

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Overview of Heat Measurement Technology for Hypersonic Vehicle Surfaces

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