基于CFD方法的固定翼无人机着陆控制建模  

The Landing Control Modeling for Fixed-Wing UAV Based on CFD Method

作　　者：郑积仕[1,2] 蒋新华[1,2] 陈兴武[2] 

机构地区：[1]中南大学信息与工程学院,湖南长沙410083 [2]福建工程学院,福建福州350108

出　　处：《信息与控制》2012年第1期51-56,共6页Information and Control

基　　金：福建省科技厅工业科技重点资助项目(2009H0002)

摘　　要：为了实现固定翼无人机低速平稳着陆的目的,以某型无人机为例,阐述以计算流体动力学(CFD)方法求解固定翼无人机气动力系数的过程,即构建飞机几何模型、设定计算域并划分网格、基于非耦合隐式求解器求解在K-E湍流模型下各飞行状态的气动系数.提出以较大迎角低速滑翔降落的着陆控制方法,基于求解的气动特性,计算飞机降落前的理想状态,并基于状态反馈的纵向控制律实现着陆控制.在Simulink环境中,基于AeroSim工具箱构建仿真程序,验证了方法的有效性.To realize the low-velocity and steady landing of the fixed-wing unmanned aerial vehicle （UAV）, the process of solving the coefficients of aerodynamic force for a fixed-wing UAV based on CFD （computational fluid dynamics） method is illustrated, taking a UAV as an example. This process includes modeling a geometry for the UAV, setting computational domain and generating meshes, and solving the coefficients of aerodynamic force in various flying statuses under K-E turbulence model based on the uncoupled implicit solver. A landing control method for keeping the UAV landing with low-velocity sliding and in a large angle of attack is proposed. Based on the solved coefficients of aerodynamic force, the right status of the pre-landing is computed, and the longitudinal control law based on the state feedback is used to realize the landing control. The simulation programme constructed on the basis of AeroSim toolbox in Simulink environment verifies the efficiency of the method.

关 键 词：CFD方法 固定翼无人机 建模 AeroSim 着陆控制 

分 类 号：V249[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]