发明名称 Verifiable Quick Patch Repair for Composite Structures
摘要 A method for patching a hole in a composite parent structure. The method comprises: inserting an insert in the hole; placing a composite patch having a multiplicity of curved flexible members on one side of the composite parent structure in a position where a central portion of the composite patch overlies the insert and the flexible members confront opposing portions of the composite parent structure providing adhesive between the composite patch, the insert, and the composite parent structure; pressing the composite patch against the composite parent structure with sufficient pressure to force the flexible members to conform to the shape of the composite parent structure; and while the flexible members are in a stressed state, curing the adhesive in a manner that causes the flexible members to bond to the parent structure.
申请公布号 US2016176177(A1) 申请公布日期 2016.06.23
申请号 US201615059321 申请日期 2016.03.03
申请人 The Boeing Company 发明人 Georgeson Gary E.;Griess Kenneth H.
分类号 B32B37/12;B32B37/10 主分类号 B32B37/12
代理机构 代理人
主权项 1. A method for patching a hole in a composite parent structure, said method comprising: inserting an insert in the hole; placing a composite patch having a multiplicity of curved flexible members on one side of the composite parent structure in a position where a central portion of the composite patch overlies the insert and the flexible members confront opposing portions of the composite parent structure disposed around the insert; providing adhesive between the composite patch and the insert, and between the composite patch and the composite parent structure; and pressing the composite patch against the composite parent structure with sufficient pressure to force the flexible members to conform to the shape of the surface of the opposing portions of the composite parent structure while the adhesive therebetween is curing.
地址 Chicago IL US