Optimization Designing On Integral Panel Of The New Aircraft Outboard Wing

The integral panel haves the advantages of low-weight, high-intensity, good airfoil shape, and so on, which have been applied in the aerospace widely. The experience enunciates that the integrated whole structure and digital manufacturing technology is the valid path that shortens developing period, lower production cost and raises the product quality, and is the foundation that the airplane is developed quickly.This paper carries on simplifying the model of the plane wing and analyzing the aerodynamic load. According to the symmetry of the load and model of the plane wing, take model of 1/4 structure. Because the ANSYS software is unwell proper in building up complicated model, so in the CATIA-3D software the first step establishment plane wing model, keep a suffix to be named the model document, lead directly in the ANSYS. In the ANSYS the establishment parameters denote respectively the height and the width of the ribs for the integral panel.In the ANSYS, with move and stress for State Variables, with the breadth and high of the rib for Design Variables, with the total weight of the whole stiffened panels is minimum for Objective Variables, sub-problem calculation method is adopted to solve the optimal design with carrying on 15 iterative operations.Make use of the optimal result to carry on the inherence frequency analysis and stability analysis towards the stiffened panel. Moreover, comparing to the original riveting panel in inherence frequency, weight, intensity and inflexibility, obviously the synthesis function of the stiffened panels is better than the original rivet joint panels, and the static strength experiment of the stiffened panels was qualified.