基于模糊逻辑方法的涵道风扇飞行器非定常气动力建模及应用  

Unsteady Aerodynamics Modeling and Application of the Ducted Fan UAV Based on Fuzzy Logic Method

作　　者：杨磊[1] 叶正寅[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2014年第6期849-856,共8页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(11272272)资助

摘　　要：为研究涵道风扇飞行器过渡阶段飞行特性,使用CFD方法,通过叶素理论和滑移网格技术,求解涵道风扇飞行器定常状态气动力及俯仰非定常状态气动力,并计算了升降舵偏角对气动力的影响。将CFD计算数据作为训练样本,使用模糊逻辑方法建立了涵道风扇飞行器纵向非定常气动力模型,该模型考虑了涵道风扇飞行器俯仰运动时的非定常效应及气动力与发动机转速的耦合效应,对涵道风扇飞行器非定常气动力具有较高精度的描述。使用该模型求解涵道风扇飞行器六自由度方程,进行时域仿真,仿真结果表明涵道风扇飞行器高度和速度的指令跟踪性能良好,低速飞行性能良好,过渡阶段姿态稳定。Based on the blade element theory and sliding meshs technique, the steady and unsteady aerodynamic forces of the ducted fan UAV are calculated by CFD, and the influences of the elevator angles on the aerodynamic force are measured.Through making use of the CFD data as the training specimen, the unsteady aerodynamic mod-els of the ducted fan UAV are set up by fuzzy logic method.These models have high accuracy and the unsteady effects of the ducted fan UAV and the coupling effects of aerodynamic and engine rotation speed are considered.Un-der the action of control system, the six degrees of freedom functions of the ducted fan UAV are solved.The time-domain simulation results and their analysis show preliminarily that the tracking performance and the low speed flight performance of the ducted fan UAV are good.

关 键 词：涵道风扇飞行器 非定常气动力模型 模糊逻辑模型 时域仿真 

分 类 号：V211.53[航空宇航科学与技术—航空宇航推进理论与工程]