Abstract:

Limited by the capacity of the test equipment, the ground wind tunnel can’t fully simulate the near space thermal environment of the hypersonic vehicle. The longtime high temperature heat sensor was installed on the surface of the aircraft. For the first time in china, the characteristics of heat flux density time-varying data and boundary layer transition in the hypersonic vehicle above Ma 12 was obtained. The measured heat flow value is the same as the theoretical prediction value, and the deviation is less than 20%. Theoretical calculation of the internal temperature of resin based composites is higher than actual value, by the method of adding physical property parameters with temperature variation and the thermal conductivity in the heat conduction differential equation of resin matrix. And the internal stratified temperature and thickness of carbonization layer were calculated. Compared with the measured results, the deviation between the calculated value and measured result is less than 70℃, but the calculated value is higher than measured result and the maximum deviationis 275~320℃, when the thermal conductivity and physical property parameters with temperature variation are not considered.

Key words: reentry vehicle, measured heat flux density, transition characteristics, stratified temperature, thickness of carbonization layer