摘要
为了实现对飞机尾涡的有效监测,解决机场飞行安全与跑道容量受限的问题,提出了一种基于激光雷达回波的飞机尾涡参量提取算法.从尾涡的物理模型出发研究飞机尾涡的涡旋环量、径向速度分布等参量,对尾涡结构进行描述.依据尾涡参量的性质,给出了参量提取算法的设计流程,即对回波信号进行分解除噪等处理;通过选取门限确定正负速度包络,进而得到径向速度分布;利用径向速度分布反演得到涡核半径、涡核位置及涡旋环量等尾涡参量.最后以某型飞机的激光雷达探测实验数据为例进行了实例计算并与模型仿真结果进行对比,验证了该算法的有效性.
In order to realize the monitoring of the aircraft wake vortex effectively, solve the puzzles of flight safety and runway capacity limitation, an algorithm of wake vortex parameter extrication based on Lidar echo is proposed. The physical model of circulation and radial velocity distribution is studied, and the structure of wake vortex is descripted. Based on the features of the vortex parameters, the flowchart of parameter extrication is given, as echo signal processing for noise reduction, threshold selection for velocity envelopes to resolve the velocity distribution and parameter （core radius, core position, circulation） extrication. Moreover, the calculation example of extrication algorithm is carried by taking a certain type of aircraft for example which is compared with the model simulation. The experimental result verifies the effectiveness of the extrication algorithm.
出处
《光子学报》
EI
CAS
CSCD
北大核心
2013年第1期54-58,共5页
Acta Photonica Sinica
基金
国家自然科学基金(No.60672154)
安徽省自然科学基金(No.10040606Q61)资助
关键词
飞机尾涡
激光雷达
参量提取
飞行安全
跑道容量
Aircraft wake vortex
Laser detection and ranging（I.idar）
Parameter extrication
Flight safety
Runway capacity
