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 effectively monitor the tail vortex of the aircraft and solve the problem of limited airport flight safety and runway capacity, a tail vortex parameter extraction algorithm based on lidar echoes is proposed.From the physical model of tail vortex, the tail vortex The vortex ring volume, radial velocity distribution and other parameters, the wake vortex structure is described.According to the nature of the tail vortex parameters, the design flow of the parameter extraction algorithm is given, that is, the echo signal is decomposed and denoised, The envelope of the positive and negative velocities is chosen to obtain the radial velocity distribution, and the vortex shedding parameters such as the radius of the vortex core, the position of the vortex core and the vortex ring volume are obtained by using the radial velocity distribution.Finally, The experimental data are taken as an example to calculate and compare with the simulation results of the model to verify the effectiveness of the algorithm.