摘要
微型飞行器(MAV)非线性飞行力学模型研究是MAV设计中的一个重要环节。微型涵道飞行器由于大包线、尺寸小、速度低、气动布局特殊,其飞行力学特性具有显著的非线性特性。以低雷诺数风洞实验为基础,研究了微型涵道飞行器的空气动力学特性,并采用CFD方法计算了微型涵道飞行器的动导数。在此基础上建立了微型涵道飞行器的飞行力学模型,并计算了基本飞行性能和配平曲线。结果表明,微型涵道飞行器与常规飞行器相比有很大差异,可以完成悬停、垂直起降和前飞的大包线飞行。
Research on nonlinear flight dynamic mathematical model of micro air vehicles（MAV） plays an important role in MAV design.The flight dynamics of ducted fan MAV is remarkably nonlinear due to its big flight envelope,small size,low speed and special aerodynamic configuration.The aerodynamic characteristics of MAV was studied based on low Reynolds numbers wind tunnel testing,furthermore,the dynamic derivatives of the ducted fan MAV were calculated using computational fluid dynamics（CFD） method.The flight dynamic mathematical model of MAV was established based on aerodynamic characteristics,and its basic flight performance and trim results were calculated.The results indicate that the ducted fan MAV is different from conventional aircraft,it can hover,take off and landing vertically and fly forward.
出处
《飞行力学》
CSCD
北大核心
2012年第3期197-200,共4页
Flight Dynamics
基金
国防预研基金资助项目
关键词
微型飞行器
飞行力学
非线性
动导数
配平
micro air vehicle
flight dynamics
nonlinearity
dynamic derivative
trim
