机翼部段静力试验优化设计方法

Optimum design method for static test of aircraft wing segment

飞机结构部段结构静力试验是验证结构承载能力、有限元模型等设计指标的重要手段。部段试验相比全机试验规模较小,但需要解决边界分离面刚度匹配、支持模拟、加载模拟等技术难题,保证结构考核精度不受影响。某型飞机机翼为联翼式桁架布局,取中间一段机翼进行静力试验,需要解决多分离面优化设计,气动惯性载荷优化设计及施加等问题。采用分级解耦的设计思想,将试验设计的各个影响因素逐级剥离并建立相应的分析对比模型,依据结构响应误差进行优化设计,评估每一级简化模拟带来的误差。以结构有限元数值仿真为基础,提出了多铰支接头位移+主动载荷混合边界模拟,分离面加载假件刚度解耦设计与优化,桁架式机翼载荷优化设计及载荷施加等试验技术,使部段试验设计精度达到较高水平。

Aircraft component static test is an important means to verify structure carrying capacity and finite element models.The component test has a fairly small scale compared with full scale static tests.However,the separation surface stiffness mapping,support simulation and load simulation problems need to be solved to ensure that the accu⁃racy of structural assessment is not affected.The static test on the middle wing section of an aircraft with a combined wing layout is conducted,which requires the solution to the multi-separation surface optimum design,aerodynamic load and inertial load optimum design and application.We adopt the design idea of hierarchical decoupling,stripping each influence factor of the test design step by step and establishing corresponding models for comparison analysis.Optimum design is carried out according to the structure responding error to evaluate errors from each simplified simu⁃lation.Based on the structural finite element numerical simulation analysis,we propose test techniques such as the multi-hinged joint displacement and active load hybrid simulation,stiffness decoupling optimum design of the separa⁃tion surface loading replacement part,load optimum design and application of truss wings to achieve a higher preci⁃sion level of the component test design.