微扑翼飞行器总体设计及实验  

Integrated design and experimental study of FMAV

作　　者：苏进展[1] 方宗德[1] 刘岚[1] 

机构地区：[1]西北工业大学机电学院,陕西西安710072

出　　处：《光学精密工程》2008年第4期656-661,共6页Optics and Precision Engineering

基　　金：国家自然科学基金资助项目(No.50575183);高等学校博士学科点专项科研基金资助项目(No.20050699022)

摘　　要：提出了适合工程实际的微扑翼飞行器的设计方法。利用几何相似原理,拟合了以翼展为基本参数的仿生公式,并确定了飞行参数、结构参数和动力参数。根据初步的仿生设计结果,进行传动结构、翅翼尾翼等总体结构设计,并按照运动学分析、气动力分析、动力学分析相结合的动态分析方法研究了扑翼样机理论上产生的升力。与风洞实验结果比较表明,平均升力误差为0.61 g,基本满足设计要求,为微扑翼飞行器的研制提供了理论和实验依据。A new design method for a Flapping Micro Air Vehicle（FMAV） was proposed based on the background of engineering application. By the geometric similarity principle, the biomimetic formulas were deduced based on wingspan, and the flight parameters, structure parameters and dynamic pa- rameters were determined. According to the previous biomimetic results, the transmission layout, wings and the empennages were designed, then the dynamic analysis method including kinematic, aerodynamic and structure dynamic analysis was applied to the FMAV to calculate the lift force in theory. The calculated results show that the average force error is 0.61 g compared with the results of wind tunnel test,which proves that the method and parameters of design can satisfy the design requirements, and can provide theoretical and experimental basis for the research and manufacture of FMAV.

关 键 词：微扑翼飞行器 总体设计 动态分析 风洞实验 

分 类 号：V276[航空宇航科学与技术—飞行器设计]