混合缩比连续翼型设计方法  

Design Methods of Continuous Deformable Hybrid Airfoils

作　　者：李钊 杨广珺[2] 孙静[1,3] 肖京平 蒋锋[1] LI Zhao;YANG Guangjun;SUN Jing;XIAO Jingping;JIANG Feng(School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China;National Key Laboratory of Science and Technology on UAV,Northwestern Polytechnical University,Xi'an 710068,China;Institute of Low Speed,China Aerodynamics Research and Development Centre,Mianyang 621000,China)

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]西北工业大学无人机特种技术国防科技重点实验室,陕西西安710068 [3]中国空气动力研究与发展中心低速所,四川绵阳621000

出　　处：《飞机设计》2021年第2期17-21,共5页Aircraft Design

基　　金：装备预先研究项目(41406020501)。

摘　　要：对于飞机的结冰风洞试验,采用多控制点的遗传优化算法进行混合缩比翼型设计。以混合翼型与全尺寸机翼在前缘范围的压力系数相同为目标,通过数值计算分析翼型气动特性,并对比多种优化策略,改进优化算法,生成不同迎角下的混合翼型。以铝合金为材料考察了混合翼型蒙皮变形能力,计算得到蒙皮最大应力为500 MPa,超过其抗拉强度。最终采用分段蒙皮的方式实现混合翼型变形功能。For the aircraft icing wind tunnel test,the multi-control-point genetic algorithm is used to design the hybrid scale airfoil.Aiming at the same pressure coefficient of the hybrid airfoil and the full-scale airfoil in the leading edge range,the aerodynamic characteristics of the airfoil are analyzed by numerical calculation and compared with a variety of optimization strategies.The optimization algorithm is improved to generate the hybrid airfoil at different angles of attack.The deformation ability of the skin of the hybrid airfoil is investigated with aluminum alloy as the material,and the maximum stress of the skin is calculated to be 500 MPa,which exceeds its tensile strength.Finally,the method of segmented skin is used to realize the deformation function of hybrid airfoil.

关 键 词：结冰风洞 混合缩比 遗传算法 翼型 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]