The effect of detector installing structure on wall temperature measurement of vehicle
-
摘要: 针对飞行试验中飞行器薄壁壳体测量温度与预测温度存在较大差异这一问题,采用气动热工程算法结合热传导计算方法,分析了测温探测器安装结构对测点温度的影响,并提出了改进措施。结果表明:对于薄壁结构飞行器在上升段有气动加热、其表面处于升温过程或热量由壳体表面向内部传导时,测温探测器安装结构对测点温度基本无影响。但当飞行器处于飞行中段,在辐射散热、表面温度低于壳体内部温度造成热量由壳体内部向外表面传导时,测点温度受原探测器安装结构影响明显,测量温度明显低于不装探测器时的预测温度;而采用本文提出的探测器安装方案,可明显降低对测点温度的影响,在飞行器的测点位置最大影响小于0.5K。Abstract: The effect of the detector installing structure on the measured point temperature is analyzed using engineering aero-thermodynamics and heat conduction computation. To diminish the effect, a temperature detector installing structure is brought out according to the vehicle shell structure. The result shows that the installing structure has no effect on the measurement point temperature when the surface temperature is rising or heat is transmitting from the surface to the interior. However, the measurement temperature using the original installing structure is obviously lower than the predicted point temperature without the detector when heat is transmitting from the interior to the surface during the flight middle course. The temperature detector installing structure proposed in the paper can greatly reduce the structure effect on the measured point temperature:the maximum deviation of the temperature due to the presence of the detector is less than 0.5K.
-
Key words:
- temperature /
- aero-thermodynamics /
- heat conduction /
- shell structure /
- flight middle course
-
表 1 防热材料物性参数
Table 1. Parameters of glass fiber reinforced plastics
红外发射率 密度/(kg·m-3) 导热系数/(W·(m·K)-1) 比热/(J·(kg·K)-1) 0.85 1750 0.44 1000 表 2 铝合金物性参数
Table 2. Parameters of aluminum alloy
温度/K 298 373 423 473 523 573 比热/(J·(kg-1·K)-1) 921 921 1005 1047 1089 1089 密度/(kg·m-3) 2640 导热系数/(W·(m·K)-1) 125.6 -
[1] 陈鑫, 刘莉, 李昱霖, 等. 高超声速飞行器翼面气动加热、辐射换热与瞬态热传导的耦合分析[J]. 弹道学报, 2014, 26(2): 1-5. http://www.cnki.com.cn/Article/CJFDTOTAL-DDXB201402002.htmChen X, Liu L, Li Y L, et al. Coupled study of aerodynamic heating, radiative heat transfer and heat conduction for airfoils of hypersonic vehicles[J]. Journal of Ballistics, 2014, 26(2): 1-5. http://www.cnki.com.cn/Article/CJFDTOTAL-DDXB201402002.htm [2] 杨荣, 王强. 高超声速旋转体气动加热、辐射换热与结构热传导的耦合数值分析[J]. 上海航天, 2009, (4): 25-29. http://www.cnki.com.cn/Article/CJFDTOTAL-SHHT200904009.htmYang R, Wang Q. Coupled numerical study on aero-heating, radiative heat transfer and structure heat conduction for hypersonic bodies of revolution[J]. Aerospace Shanghai. 2009, (4): 25-29. http://www.cnki.com.cn/Article/CJFDTOTAL-SHHT200904009.htm [3] 王政. 飞机机翼热控方案研究及热管传热特性分析[D]. 南京: 南京航空航天大学, 2009. http://cdmd.cnki.com.cn/article/cdmd-10287-1011253497.htmWang Z. Study on thermal control scheme of aircraft wing and analysis of heat transfer characteristics of heat pipe[D]. Nanjing: Nanjing University of Aeronautics&Astronautics, 2009. http://cdmd.cnki.com.cn/article/cdmd-10287-1011253497.htm [4] Engel C D. Miniver upgrade for the avid system, Vol.1: Lanmin user's manual[R]. NASA CR-172212, 1983. [5] 戎宜生, 刘伟强. 过渡流区钝锥体Linear桥函数调节参数研究[J]. 物理学报, 2012, 61(4): 1-5. http://www.cnki.com.cn/Article/CJFDTOTAL-WLXB201204011.htmRong Y S, Liu W Q. Research on accommodation parameter of linear bridging relation for blunt cone in transitional regime[J]. Acta Physica Sinica, 2012, 64(4): 1-5. http://www.cnki.com.cn/Article/CJFDTOTAL-WLXB201204011.htm [6] Fay J A, Riddell F R. Theory of stagnation point heat transfer in dissociated air[J]. J Aero Sci, 1958, 25(2): 73-85. doi: 10.2514/8.7517 [7] Lees L. Laminar heat transfer over blunt nosed bodies at hypersonic flight speed[J]. Jet Propulsion, 1956, 26(4): 259-269. doi: 10.2514/8.6977 [8] 张志成, 潘梅林, 刘初平, 等. 高超声速气动热和热防护[M]. 北京: 国防工业出版社, 2003.Zhang Z C, Pan M L, Liu C P, et al. Hypersonic heating and thermal protection[M]. Beijing: Defense Industry Press, 2003. [9] Chen K K. Three dimensional nosetip shape changes in hypersonic flow. Part 1: Illustration of a mathematical model-characteristic method[R]. AIAA-73-0762, 1973. [10] Baker R L. Low temperature ablator nosetip shape change at angle of attack[R]. AIAA-72-90, 1972. [11] 王友良, 孙新川, 程相飞. 飞机机身结构温度测量[J]. 飞行试验, 2003, 19(2): 15-17.Wang Y L, Sun X C, Cheng X F. Aircraft fuselage structural temperature measurement[J]. Aviation Experiment, 2003, 19(2): 15-17. [12] 北京航空航天大学. 碳纤维复合材料高速飞行器整流罩表面瞬态温度测量装置: 中国, CN200610113792.9[P]. 2006-10-11Beijing University of Aeronautics&Astronautics. Surface temperature measuring apparatus for high speed vehicle fairing made by carbon fiber composite material: China, CN200610113792.9[P]. 2006-10-11. [13] 徐顺生, 时章明, 杨刚. 基于传热原理的热电偶测温误差模型及应用[J]. 传感器与微系统, 2006, 25(5): 15-18. http://www.cnki.com.cn/Article/CJFDTOTAL-CGQJ200605004.htmXu S S, Shi Z M, Yang G. Error model and application of temperature measure about thermo-couple based on heat transfer principle[J]. Transducer and Micro System Technologies, 2006, 25(5): 15-17. http://www.cnki.com.cn/Article/CJFDTOTAL-CGQJ200605004.htm