METHOD TO ELIMINATE UNDULATIONS IN A COMPOSITE PANEL
摘要
A method and article of manufacture of joining a stringer to a wing or tail panel and curing a wing or tail panel is disclosed. A sheet of titanium is placed between a cured stringer and an uncured wing or tail panel. The stringer, wing or tail panel and sheet are then placed within a vacuum bag, and gas is pumped out of the bag. The bag is then placed in an auto-clave to cure the wing or tail panel.
申请公布号
WO2006112823(A1)
申请公布日期
2006.10.26
申请号
WO2005US12699
申请日期
2005.04.13
申请人
THE BOEING COMPANY;PHAM, DOAN, D.;LEE, MICHAEL, A.