摘要
系统地介绍了微型飞行器的定义、类型、任务和国内外发展现状,提出了现在微型飞行器设计的技术难点,即在气动力计算时,经典的空气动力学不再适用以及缺乏小展弦比机翼在低雷诺数下飞行的试验数据,针对这一难点提出了一套系统的设计方案,分为3个部分,分别是气动力建模、多学科优化和仿真与试验。在气动力建模中采用试验与数值计算相结合的设计方法,在基础试验数据的粗略估算后进行CFD计算达到准确设计的效果。在多学科优化中重点对续航能力进行了优化。最后通过比较仿真的结果和原型机飞行试验的数据对设计进行了验证和反馈。此套设计方法适用于大多数微型飞行器的设计。
The definition,classification and function of the Micro Air Vehicle（MAV） are introduced as well as its developing status in the world.The technical difficulty of MAV design is put forward,that is the classic aerodynamics is no longer applicable under a serious influence of low Reynolds numbers,and flight test data of low aspect ratio wing is lacked.According to that difficulty,a systematic design scheme is proposed that includes aerodynamic modeling,multi-disciplinary optimization and simulation and testing.Numerical calculation combined with experiment is used in aerodynamic modeling.Multi-disciplinary optimization is emphasized on the capacity of endurance,and finally,the design verification and feedback by comparing simulation results and prototype flight testing data.This design method applies to most MAV design.
出处
《飞机设计》
2010年第6期11-16,共6页
Aircraft Design
