面向初步设计的一种高效静气动弹性分析方法  

A High-efficiency Method for Static Aeroelasticity Analysis in Preliminary Design

作　　者：赵冉 陶杨 张峻鸣 蒋盼盼 王国良 谷迎松[1] ZHAO Ran;TAO Yang;ZHANG Junming;JIANG Panpan;WANG Guoliang;GU Yingsong(School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China;Unit 92728 of PLA,Shanghai 200436,China;Jiangxi Hongdu Aviation Industry Group Co.,Ltd.,Nanchang 330024,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]92728部队,上海200436 [3]江西洪都航空工业集团有限责任公司,南昌330024

出　　处：《机械科学与技术》2024年第5期891-896,共6页Mechanical Science and Technology for Aerospace Engineering

基　　金：陕西省自然科学基础研究计划(2022JM-047)。

摘　　要：大展弦比柔性机翼在气动载荷作用下会发生弹性变形从而引起气动特性变化,因此在初步设计阶段,希望使用一种高效分析方法研究静气动弹性平衡下机翼气动载荷的重新分布情况。本文提供了一种求解静气动弹性变形和对应气动载荷的高效方法,即采取松耦合策略,假设攻角不变,将未变形状态的载荷加载到结构上,计算出结构变形,再由变形后的气动外形计算气动载荷分布,反复迭代至变形/载荷收敛,得到机翼最终气动弹性载荷分布情况和气动特性。采用大展弦比弹性模型飞机算例表明了该方法的可行性。Flexible wings with large aspect ratio undergo elastic deformation under aerodynamic loads,resulting in changes of wing's aerodynamic characteristics.Therefore,in the preliminary design stage,it is expected to adopt a fast and efficient calculation method to study the redistribution of wing's aerodynamic load under static aeroelastic equilibrium.This work provides an efficient analysis method to solve the static aeroelastic deformation and the corresponding aerodynamic load,in which a loose coupling strategy is adopted,assuming that the angle of attack is unchanged.The undeformed load is first applied on the wing structure,the structural deformation is calculated,and then the aerodynamic load redistribution is calculated from the deformed aerodynamic shape.The final aeroelastic load distribution and aerodynamic characteristics of the wing are obtained by iterating repeatedly until the deformation/load converged.The feasibility of the method is demonstrated by a large aspect ratio elastic model aircraft.

关 键 词：初步设计 大展弦比 静气动弹性 松耦合 载荷 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]