基于响应面和遗传算法的尾座式无人机结构参数优化  

Optimization of Configuration Parameters of Tail-sitter UAV Based on Response Surface and Genetic Algorithm

作　　者：刘文帅[1,2] 姚小敏 李超群[1,2] 张梦飞 淡煦珈 韩文霆 LIU Wenshuai;YAO Xiaomin;LI Chaoqun;ZHANG Mengfei;DAN Xujia;HAN Wenting(College of Mechanical and Electronic Engineering,Northwest A&F University,Yangling,Shaanxi 712100,China;Key Laboratory of Agricultural Soil and Water Engineering in Arid and Semiarid Areas,Ministry of Education,Northwest A&F University,Yangling,Shaanxi 712100,China;Nanjing Hepu Aero Science and Technology Co.,Ltd.,Nanjing 211300,China;Institute of Soil and Water Conservation,Northwest A&F University,Yangling,Shaanxi 712100,China)

机构地区：[1]西北农林科技大学机械与电子工程学院,陕西杨凌712100 [2]西北农林科技大学旱区农业水土工程教育部重点实验室,陕西杨凌712100 [3]南京禾谱航空科技有限公司,南京211300 [4]西北农林科技大学水土保持研究所,陕西杨凌712100

出　　处：《农业机械学报》2019年第5期88-95,共8页Transactions of the Chinese Society for Agricultural Machinery

基　　金：国家重点研发计划项目(2017YFC0403203);杨凌示范区产学研用协同创新重大项目(2018CXY-23);高等学校学科创新引智计划项目(B12007)

摘　　要：设计了一种垂直起降尾座式无人机,利用中心组合试验(Central composite design,CCD)对无人机的翼展长、后掠角、小翼高和小翼厚4个结构参数进行设计,构建了25组样本点。利用ANSYS CFX进行升阻比和阻力数值模拟,通过Design-Expert软件建立无人机结构参数与升阻比、阻力的响应面模型,其中升阻比随着翼展长和小翼高的增加而增大,后掠角和小翼高对升阻比的影响较小,当攻角为4°～8°时,升阻比随小翼厚的增加而减小,当攻角为10°～12°时,升阻比随小翼厚的增加而增大;阻力随着翼展长和小翼厚的增加而增大,随小翼高的增加而减小,随后掠角的增加先增大后减小。以升阻比最大和阻力最小为优化目标,采用多目标遗传算法进行结构参数优化,得到最优结构参数为:翼展长1 123 mm、后掠角34°、小翼高39 mm、小翼厚3 mm,与原始样机相比升阻比提高了12. 4%,阻力降低了5. 3%。采用风洞试验对响应面模型进行了验证,其中升阻比和阻力的数值模拟相对误差小于8. 0%,响应面模型相对误差小于3%,表明响应面模型具有较高的精度和良好的通用性,可用于垂直起降尾座式无人机的优化设计。An agricultural vertical take-off and landing (VTOL) tail-sitter UAV with symmetrical winglets and wings was designed. The main parameters of the tai-sitter, wingspan, sweep angle, winglet height and winglet thickness were investigated to optimize the structure design. Central composite design (CCD) was employed to construct 25 sample points. Numerical simulation of lift drag ratio and drag were carried out with ANSYS CFX. The response surface models (RSM) of UAV structure parameters with lift drag ratio and drag were established by Design-Expert software. The lift drag ratio was increased with the increase of wing length and height of winglet. The lift drag ratio was decreased with the increase of wing thickness at attack angle of 4°~8°, and with the decrease of wing thickness at attack angle of 10°~12°. The impact of sweep angle and wing height on the lift drag ratio was small. The drag was increased with the increase of wing length and thickness of wing, and decreased with the increase of winglet height. The drag was increased firstly with the increase of sweep angle and then decreased. The multi-objective genetic algorithm was used to optimize the structural parameters, with maximum lift drag ratio and minimum drag as optimal objects. The optimal structural parameters were wingspan of 1 123 mm, sweep angle of 34°, wing height of 39 mm, and wing thickness of 3 mm. Compared with the original configuration, the average lift drag ratio was improved by 12.4%, while the average drag was reduced by 5.3%. The response surface model was validated by wind tunnel test. The numerical simulation error of lift drag ratio and drag was less than 8.0%, and the error of response surface model was less than 3%. It was shown that the response surface model had high accuracy and good versatility, and it can be used in the optimization design of vertical takeoff and landing of tailstock UAV. The results were of great significance for the design of tail-sitter UAV.

关 键 词：尾座式无人机 结构优化 遗传算法 响应面 

分 类 号：S24[农业科学—农业电气化与自动化]