飞机尾涡扫描特性与涡核位置估算方法改进  

Aircraft Wake Vortex Scanning Characteristics and Improvement of Vortex Core Position Estimation Method

作　　者：谷润平[1] 鹿彤 Gu Runping;Lu Tong(CAUCCollege,Air Traf fic Management,Tianjin 300300,China)

机构地区：[1]中国民航大学空中交通管理学院,天津300300

出　　处：《应用激光》2023年第10期156-163,共8页Applied Laser

基　　金：国家自然科学基金资助(U2133210);中央高校基本科研任务费项目(3122021066)。

摘　　要：飞机尾流涡核的精准辨识是动态缩减尾流间隔的前提。首先建立了尾涡流场演变模型,对尾涡流场进行了仿真;之后对不同强度和高度的尾涡组合速度场探测结果进行仿真分析;最后提出了涡核位置估算的“极大-次大值”法,提高了对涡核位置识别的准确度。研究表明:标准差两峰值处极大值与次大值之差越大,则涡核与最大标准差对应的距离门越接近;在代入的算例验证中,径向距离估算结果偏差不超过1.5 m,且涡核位置偏差程度均在3 m以内;相比极差法和梯度法,位置偏差修正了60%及以上,最高可达86%。The accurate identification of aircraft wake vortex core is the premise of dynamically reducing the wake interval.Firstly,the evolution model of the wake vortex field was established,and the wake vortex field was simulated.Secondly,the simulation analysis was carried out on the combined wake vortex velocity field detection results of different intensities and heights.Finally,the"Maximum-Submaximum"method of vortex core position estimation was proposed to improve the accuracy of vortex core position recognition.The research shows that the larger the difference between the maximum and the second maximum at the two peaks of standard deviation is,the closer the distance gate corresponding to the vortex core and the maximum standard deviation is.In the verification of the substituted example,the deviation of the radial distance estimation results is not more than 1.5 m,and the deviation of the vortex core position is within 3 m.Compared with the range method and gradient method,the position deviation has been corrected by more than 60%,and the maximum is 86%.

关 键 词：激光雷达 尾流探测 尾涡位置估算 尾涡流场仿真 尾涡特征参数计算 

分 类 号：V328[航空宇航科学与技术—人机与环境工程]