期刊文献+

基于线结构光的冰横截面轮廓测量 被引量:7

Ice cross sectional profile measurement based on line structured light
下载PDF
导出
摘要 为实现冰横截面轮廓非接触测量,提出了基于线结构光的冰横截面轮廓测量方法:将面激光垂直投射在冰块上,利用摄像机拍摄冰块表面变形激光线,并根据事先标定的激光平面与摄像机间几何关系,计算冰面激光线三维坐标点,这些三维坐标点在激光平面上的投影即为冰块横截面轮廓。设计了基于线结构光的冰轮廓测量简易装置,开发了测量程序,并针对冰面激光线反射能量弱导致的激光线图像对比度低的问题,研究了冰面激光中心线提取方法。对冰箱冻结的已知半径圆柱冰块进行了横截面轮廓测量,平均相对误差为0.018,最大相对误差为0.052;还对二元翼型结冰冰块进行了横截面轮廓测量,得到了初步测量结果;为开展结冰试验中结冰生长过程冰形在线三维测量奠定了技术基础。 To realize the ice cross sectional profile measurement in a non-contact way,a line structured light based measurement is adopted.Firstly a laser sheet is projected vertically on the ice surface.Secondly,the image of the deformed laser line on the ice surface is captured by a camera.Finally,the 3Dcoordinates of the laser line on the ice surface are calculated upon the calibrated geometric relationship between the laser sheet and the camera.Then the projection of these 3Dcoordinates on the laser sheet is the ice cross sectional profile.In this paper,a simple line structured light measurement device and a measurement procedure are developed.To deal with the problem of the low image contrast due to the low reflected laser energy on ice,a novel laser line center extraction method is provided.In the experiments,an ice sheet frozen by a refrigerator with its radius known is measured.The maximum relative error is 0.052,and the mean relative error is 0.018.A preliminary measurement result of the icing on two elements airfoil generated in an icing wind tunnel is also obtained.It lays a technical foundation for the 3Dice shape online measurement during ice accretion in icing wind tunnels in the future.
出处 《实验流体力学》 CAS CSCD 北大核心 2016年第3期14-20,共7页 Journal of Experiments in Fluid Mechanics
基金 国家自然科学基金(11272338,11472296) 国家重点基础研究发展计划(2015CB755800)项目
关键词 结冰 轮廓测量 线结构光 非接触测量 图像处理 icing profile measurement line structured light non-contact measurement image processing
  • 相关文献

参考文献18

二级参考文献42

  • 1Messinger B L. Equilibrium Temperature of an Unheated Icing Surface as a Function of Airspeed. Journal of the Aeronautical Science, 1953, 20(1): 29-42. 被引量:1
  • 2Kind R J, Potapczuk MG, Feo A, et al. Experimental and Computational Simulation of In-Flight Icing Phenomena. Progress in Aerospace Sciences, 1998, 34:257 -345. 被引量:1
  • 3Olsen W, Walker E. Experimental Evidence for Modifying the Current Physical Model for Ice Accretion on Aircraft Surfaces. NASA TM-87184, 1986. 被引量:1
  • 4Myers TG. An Extension to the Messinger Model for Aircraft Icing. AIAA Journal, 2001, 39(2): 211-218. 被引量:1
  • 5Karev AR, Farzaneh M, Lozowski EP. Character and Stability of a Wind-Driven Supercooled Water Fihn on an Icing Surface--Ⅰ. Laminar Heat Transfer. International Journal of Thermal Sciences, 2003, 42:481- 498. 被引量:1
  • 6Frank T L, Abdollah K. Effects of ice accretions on aircraft aerodynamics[J]. Progress in Aerospace Sciences, 2001,37 (8) :669- 767. 被引量:1
  • 7Bragg M B,Broeren A P,Blumenthal L A. Iced airfoil aerodynamics [J]. Progress in Aerospace Sciences, 2005,41 (5) :323-362. 被引量:1
  • 8Kind R J, Potapczuk M G. Experimental and computational simulation of in-flight icing phenomena [J]. Progress in Aerospace Sciences,1998,34(5-6) :275- 345. 被引量:1
  • 9Cebeci T, Kafyeke F. Aircraft icing[J].Annual Review of Fluid Mechanics, 2003,35(1):11- 21. 被引量:1
  • 10Potapczuk M G. A review of NASA Lewis' development plans for computational simulation of aireraft ieing [R]. AIAA-99-0243,1999. 被引量:1

共引文献69

同被引文献76

引证文献7

二级引证文献27

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部