Boundary Layer Transition Flight Measurement and Implementation

doi:10.12382/bgxb.2021.0523

Abstract

Abstract: 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.

Key words: boundarylayertransition, flighttest, thermal-vibrationtest, calorimeterinstrument

CLC Number:

OU Chao, LONG Yaosong, YANG Qingtao, XIAO Hanshan, ZHOU Yu, YANG Kai. Boundary Layer Transition Flight Measurement and Implementation[J]. Acta Armamentarii, 2022, 43(10): 2657-2667.

References

［1］欧朝，吉洪亮，肖涵山，等.MF-1模型飞行试验结构与热防护关键问题研究[J].空气动力学学报，2017，35(5):742-749.
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，2017，35(5):742-749.(in Chinese)
[2］杨庆涛，周宇，袁先旭，等.MF-1模型飞行试验表面压力与温度测量技术研究[J].空气动力学学报，2017，35(5):732-741.
YANG Q T，ZHOU Y，YUAN X X，et al.Surface pressure and temperature measurement technology in MF-1 modelling flight test[J].Acta Aerodynamica Sinica，35(5):732-741.(in Chinese)
[3］杨庆涛，白菡尘，张涛，等.快速响应热流/温度传感器设计与特性分析[J].兵工学报，2014，35(6):927-933.
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[J].Acta Armamentarii，2014，35(6):927-933.(in Chinese)
[4］杨庆涛，王辉，朱新新，等.无水冷条件下温度与热流复合传感器设计与试验[J].兵工学报，2016，37(2):193-201.
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[J].Acta Armamentarii，2016，37(2):193-201.(in Chinese)
[5］周宇，杨庆涛，王安龄，等.MF-1飞行试验表面热流辨识[J].空气动力学学报，2019，37(6):938-944.
ZHOU Y，YANG Q T，WANG A L，et al.Estimation of surface heat flux for MF-1 flight test[J].Acta Aerodynamica Sinica，2019，37(6): 938-944.(in Chinese)
[6］钱炜祺，周宇，邵元培.表面热流辨识结果的误差分析与估计[J].空气动力学学报，2020，38(4):687-693.
QIAN W Q，ZHOU Y，SHAO Y P.Error analysis of surface heat flux estimation[J].Acta Aerodynamica Sinica，2020，38(4):687-693. (in Chinese)
[7］吴大方，赵寿根，晏震乾，等.巡航导弹防热部件热-振联合试验[J].航空动力学报，2009，24(7):7-11.
WU D F，ZHAO S G，YAN Z Q，et al. Experimental study on thermal-vibration test of thermal insulating component for cruise missile[J].Journal of Aerospace Power，2009，24(7):7-11.(in Chinese)
[8］张守言，惠宇昕.模型自由飞试验[M].北京：国防工业出版社，2002.
ZHANG S Y，HUI Y X.Modeling free flight[M].Beijing:National Defense Industry Press，2002.(in Chinese)
[9］刘浩，李晓东，杨文岐，等.考虑气动加热的翼面结构热模态试验方法研究[J].振动与冲击，2015，34(13):101-108.
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, 2015，34(13):101-108.(in Chinese)
[10］张治君，成竹，王琦，等.热振联合环境试验技术研究[J].实验力学，2013，28(4):30-35.
ZHANG Z J，CHENG Z，WANG Q，et al.Experimental technology study for thermo-vibration united environment[J].Journal of Experimental Mechanics，2013，28(4):30-35.(in Chinese)
[11］张伟，张正平，李海波，等.高超声速飞行器结构热试验技术进展[J].强度与环境，2011，38(1):1-8.
ZHANG W，ZHANG Z P，LI H B，et al.Progress on thermal test technique of hypersonic vehicle structures[J].Structure&Environment Engieering，2011，38(1):1-8.(in Chinese)
[12］杨庆涛，白涵尘，刘济春，等.变状态测量中薄壁热计后壁导热损失修正[J].航空动力学报，2015，30(2):49-55.
YANG Q T，BAI H C，LIU J C，et al.Heat conduction loss correction of thin-skin calorimeter on back surface for state-variable measurement[J］.Journal of Aerospace Power，2015，30(2): 49-55.(in Chinese)
[13］杨庆涛，白涵尘，张涛，等.隔热结构对塞块式热流测量的影响[J].实验流体力学，2014，28(5):92-98.
YANG Q T，BAI H C，ZHANG T，et al. Effects of adiabatic structure on heat flux measurement using a slug calorimeter[J].Journal of Experiments in Fluid Mechanics，2014，28(5):92-98.(in Chinese)
[14］樊会涛，郭强岭.战术导弹自主飞振动环境研究[J].战术导弹技术，2015（2）:17-22.
FAN H T，GUO Q L.Research on free flight vibration environment of tactical missiles[J].Tactical Missile Technology，2015（2）:17-22.(in Chinese)
[15］吴大方，潘兵，高镇同，等.超高温、大热流、非线性气动热环境试验模拟及测试技术研究[J].实验力学，2012，27(3):255-271.
WU D F，PAN B，GAO Z T，et al. On the experimental simulation of ultra-high temperature，high heat flux and nonlinear aerodynamic heating environment and thermo-machanical testing technique[J].Journal of Experimental Mechanics，2012，27(3):255-271.(in Chinese)
[16］吴大方，赵寿根，潘兵，等.高速巡航导弹翼面结构热-振联合试验研究[J].航空学报，2012，33(9):33-42.
WU D F，ZHAO S G，PAN B，et al.Research on thermal-vibration joint test for wing structure of high-speed cruise missile[J].Acta Aeronautica et Astronautica Sinica，2012，33(9):33-42.(in Chinese)
[17］梁德利，于开平，韩敬永.高速飞行器振动噪声环境预示技术[J].噪声与振动控制，2013，1006:58-62.
LIANG D L，YU K P，HAN J Y.Advances in noise and vibration environment prediction of high speed spacecrafts[J].Noise and Vibration Control，2013，1006:58-62.(in Chinese)
[18］ KIMMEL R L，ADAMCZAK D，JULIANO T J.IFiRE-5 flight test preliminary results[C]∥Proceedings of the 51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.Texas，US:AIAA，2013:1-16.
[19］ JULIANO T J，ADAMCZAK D，KIMMEL R L. HIFiRE-5 Flight Test Heating Analysis[C]∥Proceedings of the 52nd Aerospace Sciences Meeting.Maryland，US:AIAA，2014:1-17.
[20］ DEL VECHINO A，MARINO G，THOEMEL J，et al. EXPERT-The ESA experimental re-entry vehicle: overview of the experiments and payloads qualified and accepted for the flight[C]∥Proceedings of the 39th AIAA Fluid Dynamics Conference.Texas，US:AIAA，2009:1-16.
[21］ CONSTANTINE P G，DOOSTAN A，WANG Q，et al.A surrogate accelerated Bayesian inverse analysis of the HyShot II flight data[C]∥Proceedings of the 52nd AIAA/ASME/ASCE/AHS/ASC Structures，Structural Dynamics and Materials Conference.CO，US:AIAA，2011:1-9.