公开(公告)号：US20030167617A1

公开(公告)日：2003-09-11

申请号：US10370814

申请日：2003-02-19

Applicant: STRESSWAVE, INC.

Inventor： Eric T. Easterbrook ,  Michael A. Landy

IPC: B23P011/00 ,  B21D039/03

CPC classification number: B23P9/025 ,  B23P9/04 ,  Y10T29/49826 ,  Y10T29/49863 ,  Y10T29/49995 ,  Y10T29/53365

Abstract: A method of manufacturing a fatigue life enhanced product from a plurality of workpiece parts. At least one fatigue enhancing operation is performed on a first workpiece at a first work station. At least one fatigue enhancing operation is performed on a second workpiece at a second work station. The first and second workpieces are transferred to a first assembly station, where the workpieces are joined to form a fatigue life enhanced product. Aerostructures manufactured according to the method may include components fabricated at different locations to have fatigue life enhancing properties, especially in bounding material adjacent to holes designed to accommodate fasteners. By use of the method, the final assembly step can thus avoid the necessity to include the processing of holes to enhance fatigue life, since this step has been performed prior to bringing components into position to be joined in the final shape or assembly of the airframe.

Abstract translation: 一种从多个工件部件制造疲劳寿命增强产品的方法。 在第一工位上对第一工件执行至少一个疲劳增强操作。 在第二工作站上对第二工件执行至少一个疲劳增强操作。 第一和第二工件被转移到第一组装工位，其中工件被连接以形成疲劳寿命增强的产品。 根据该方法制造的航空结构可以包括在不同位置制造的具有疲劳寿命增强性能的部件，特别是在与设计成适应紧固件的孔相邻的边界材料中。 因此，通过使用该方法，最终组装步骤因此可以避免包括加工孔以增加疲劳寿命的必要性，因为该步骤已经在使部件进入到机身的最终形状或组装中的接合位置之前进行 。