Parametric Analysis Of The Structure Of Aircraft Panel In The Process Of Creep Age Forming

Creep age forming technology is a kind of modelling process which combines artificial aging and creep forming together. Integral panel is the main stress components of aircraft and is a important part of aircraft shape.It is the best technology currently that the creep age forming technology is applied to the forming process of the large integral panel. But there is few research in domestic, no readymade technology can be refered to.In this paper,the creep age forming process was applied to the forming process of 7075 aluminum alloy stiffened panel,we carried out the test and finite element analysis and studied the effect of rod structure and the thickness of panel to the springback of panel.Bringing some references to manufacturing of large aircraft of our country.The main research work and conclusion in this paper include:(1)The springback of 7075 aluminum alloy stiffened integral panel were less than flate panel based on the creep age forming test, it proved that the rod structure can effectively reduce the springback of panel;(2)We carried out the finite element analysis of 7075 aluminum alloy stiffened integral panel through the established finite element model and the creep constitutive model,it proved that the finite element model and the creep constitutive model can effectively stimulate the creep age forming of 7075 alluminum alloy stiffened integral panel and predict the springback of panel;(3)We established 7075 aluminum alloy stiffened integral panel with different height of rod and carried out finite element analysis by using the creep age forming constitutive mpdel we established,it proved that the increasing of the height of the rod can effectively reduce the springback of panel;(4)We also established 7075 aluminum alloy stiffened integral panel with different width of the rod and carried out finite element analysis by using the creep age forming constitutive model we established,it proved that there is little effect to the springback of the panel by changing the width of the rod.(5) We established 7075 aluminum alloy stiffened integral panel with different distribution density of the rod and carried out finite element analysis by using the creep age forming constitutive mpdel we established, it proved that with the increasing of the distribution density of the rod the springback of the panel will reduce in a small range.(6) We established 7075 aluminum alloy stiffened integral panel with different thickness of the panel and carried out finite element analysis by using the creep age forming constitutive mpdel we established,it proved that with the increasing of the thickness of the panel the springback of the panel will samller and smaller.