高声速飞行器再入过程中面临严峻的气动加热环境,最高气流温度可达上万摄氏度,常用量热计在如此高的气流温度下,缺乏良好的热流测试性能和热负荷生存能力。为解决地面试验中高超声速飞行器模型表面高热流的连续、精准测量难题,研发了一种基于微流道冷却的新型水卡式量热计,其内部微型流道结构采用3D打印技术构建。通过数值仿真,确定了新型水卡式量热计的微流道尺寸与布局,与同一冷壁热流的传统水卡式量热计相比,其核心区域温升降低近50%,验证了微流道水卡式量热计在极端热环境下的测试能力和生存能力。电弧加热射流试验结果表明:微流道水卡式量热计可以同步测量压力、温度、热流数据,实现了高温流场参数的集成化辨识,并具有良好动态响应特性;最大热流测量值超过18MW/m2,测量绝对偏差和平均偏差分别控制在3.44%与±1.72%以内。
Abstract
The aerodynamic heating environment encountered during hypersonic flight or reentry from space is severe in which the highest temperature can even reach 10000℃, resulting in a failure of commonly used calorimeterts showing great heat flux testing performance and thermal load viability .An new water calorimeter based on micro-channel cooling was developed in order to solve the problem of continuous and accurate measurement of high heat flux on the surface of high supersonic aircraft in ground test, which was prepared by 3D printing. Based on the numerical simulation, the size and configuration of the new water calorimeter was optimized. Comparing to traditional water calorimeter, the temperature rise of the core area is reduced by 50 percent under the same cold-wall heat flux, which illustrates the test and survival ability of micro-channel water calorimeter in extreme thermal environment. Finally, the arc heated jet test was carried out, which shows that the micro-channel water calorimeter could measure pressure and temperature and heat flow parameters synchronously with great local response characteristics, which could realize the integrated recognition of high temperatures flow field parameters. Furthermore, its maximum heat flow measurement range is over 18MW/m2, and the absolute deviation and average deviation of the sensor is less than 3.44% and ±1.72% respectively.
关键词
热学计量 /
微流道冷却;水卡式量热计;3D打印;电弧加热射流;集成化辨识
Key words
thermal metrology /
micro-channel cooling /
water calorimeter /
3D printing /
arc heated jet;integrated recognition
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