摘要
传统飞机机翼内部一般采用直线梁肋结构,使用曲线梁肋(SpaRibs)结构能够大大拓展机翼结构设计空间,进一步提升机翼的气动弹性性能。针对链接形状法(LSM)不易自动建模问题,提出使用投影映射方法进行2次空间转换,实现曲线梁肋机翼自动建模。基于遗传算法提出1种曲线梁肋机翼气动弹性综合优化设计方法。使用超声速偶极子格网法计算非定常气动力,采用模态法进行静气动弹性分析,在考虑颤振速度、静气动弹性变形约束的情况下,开展优化设计。某飞翼飞行器综合优化设计算例表明,使用曲线梁肋结构的机翼在重量增幅为1.321%的基础上,颤振速度可提高20.34%;在曲线梁肋构型的基础上进一步进行尺寸参数优化,在满足特定约束条件下,相较于初始构型减重21.76%;综合曲线梁肋构型参数和尺寸参数进行综合(一步)优化,相较于初始构型减重可达26.44%。使用曲线梁肋设计优化和尺寸优化相结合的情况下机翼能够有效地减轻机翼重量,为飞翼式飞行器的结构总体设计提供了一种快速有效的气动弹性综合优化设计方法。
Traditionally,the internal structure of aircraft wings is generally straight spars and ribs.The use of curvilinear spars and ribs(SpaRibs)can greatly broaden the design space of the aircraft wing structure and further improve the aeroelastic performance of the aircraft wing.Since the linked shape method(LSM)is not easy to automatically model,the projection mapping method was proposed to perform two space transformations to realize the automatic modelling of the SpaRibs.Based on genetic algorithm,an aeroelastic comprehensive optimization design method was proposed for aircraft wings with SpaRibs.The supersonic doublet-lattice method was used to calculate the unsteady aerodynamics,and the modal method was used for the static aeroelastic analysis.The optimal design was carried out by considering the flutter velocity and static aeroelastic deformation constraints.A comprehensive optimization design calculation example of a flying wing aircraft shows that the flutter velocity can be increased by 20.34%on the basis of a weight increase of 1.321%for a wing with a SpaRibs structure.The size parameters are further optimized on the basis of the SpaRibs configuration.Under certain constraints,the weight reduction is 21.76%compared with the initial configuration;the comprehensive(one-step)optimization of the SpaRibs configuration parameters and size parameters is combined,and the weight reduction can reach 26.44%compared with the initial configuration.The weight of the aircraft wing can be effectively reduced by combining SpaRibs design optimization and size optimization,which provides a fast and effective aeroelastic comprehensive optimization design method for the overall design of the flying wing aircraft structure.
作者
周泉知
杨佑绪
孙录斌
张兴翠
吴逸飞
霍梦文
ZHOU Quanzhi;YANG Youxu;SUN Lubin;ZHANG Xingcui;WU Yifei;HUO Mengwen(School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)
出处
《北京航空航天大学学报》
北大核心
2025年第6期2148-2156,共9页
Journal of Beijing University of Aeronautics and Astronautics
基金
江西省“双千计划”人才项目(CK202006470)。
关键词
曲线梁肋
气动弹性
飞翼
优化设计
构型设计
初步设计
curvilinear spars and ribs
aeroelasticity
flying wing
optimization design
configuration design
preliminary design
作者简介
通信作者:杨佑绪.E-mail:zgdy_1@163.com。
