Boundary Layer Transition Flight Measurement and Implementation

被引：0

作者：

Ou C. ^{[1
,2
]}

Long Y. ^{[1
]}

Yang Q. ^{[3
]}

Xiao H. ^{[2
]}

Zhou Y. ^{[4
]}

Yang K. ^{[3
]}

机构：

[1] School of Aerospace Engineering, Huazhong University of Science and Technology, Hubei, Wuhan

[2] Aerospace Technology Institute of China Aerodynamics Research and Development Center, Sichuan, Mianyang

[3] Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Sichuan, Mianyang

[4] Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Sichuan, Mianyang

来源：

Binggong Xuebao/Acta Armamentarii | 2022年 / 43卷 / 10期

关键词：

boundary layer transition; calorimeter instrument; flight test; thermal-vibration test;

D O I：

10.12382/bgxb.2021.0523

中图分类号：

学科分类号：

摘要：

For the needs of hypersonic boundary layer transition flight test and research, through integrating the variable thickness thin wall temperature test and heat flow identification method, where thin wall temperature measurement is used to identify the surface heat flux, then aircraft surface transition position can be measured. Considering the requirements of surface aerodynamic heating and the vibration environment during the high speed flight of the aircraft, the integrated module of the measuring structure and the aircraft structure is designed to improve the overall load resistance of the measuring structure. The thermal-vibration test system is to test the thermal measuring components under the ground simulation condition of flight state, and the safety and reliability of the measuring structure are verified. The results of ground thermal-vibration and flight tests show that the transition measuring structure can withstand the aerodynamic heating and vibration environment under flight conditions, respond quickly to and accurately reflect the changes of heat flow in the aerodynamic heating environment, and accurately capture the hypersonic boundary layer transition phenomenon under flight conditions. The measured data can provide calibration data for the prediction and calculation model of hypersonic transition. © 2022 China Ordnance Society. All rights reserved.

引用

页码：2657 / 2667

页数：10

共 21 条

[1] OU C, JI H L, XIAO H S, Et al., Key problems in structure and thermal protection for MF-1 model testing flight vehicle [J], Acta Aerodynamica Sinica, 35, 5, pp. 742-749, (2017)
[2] YANG Q T, ZHOU Y, YUAN X X, Et al., Surface pressure and temperature measurement technology in MF-1 modelling flight test, Acta Aerodynamica Sinica, 35, 5, pp. 732-741
[3] YANG Q T, BAI H C, ZHANG T, Et al., Design and response characteristics analysis of a fast-response sensor for temperature and heat flux measurement, Acta Armamentarii, 35, 6, pp. 927-933, (2014)
[4] YANG Q T, WANG H, ZHU X X, Et al., Design and test of a hybrid sensor for temperature and heat flux measurement without water-cooling, Acta Armamentarii, 37, 2, pp. 193-201, (2016)
[5] ZHOU Y, YANG Q T, WANG A L, Et al., Estimation of surface heat flux for MF-1 flight test [ J], Acta Aerodynamica Sinica, 37, 6, pp. 938-944, (2019)
[6] QIAN W Q, ZHOU Y, SHAO Y P., Error analysis of surface heat flux estimation [ J], Acta Aerodynamica Sinica, 38, 4, pp. 687-693, (2020)
[7] WU D F, ZHAO S G, YAN Z Q, Et al., Experimental study on thermal-vibration test of thermal insulating component for cruise missile, Journal of Aerospace Power, 24, 7, pp. 7-11, (2009)
[8] ZHANG S Y, HUI Y X., Modeling free flight, (2002)
[9] LIU H, LIU X D, YANG W Q, Et al., Thermal modal test method for a wing structure considering aerodynamic heating [ J], Journal of Vibration and Shock, 34, 13, pp. 101-108, (2015)
[10] ZHANG Z J, CHENG Z, WANG Q, Et al., Experimental technology study for thermo-vibration united environment [ J], Journal of Experimental Mechanics, 28, 4, pp. 30-35, (2013)

← 1 2 3 →