Process and tooling for reducing thermally induced residual stresses and shape distortions in monolithic composite structures
US7780899B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 8, 2004 |
| Grant date | Aug 24, 2010 |
| Priority date | — |
| Expiry date | Jul 24, 2024 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB29L2031/3076
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
Process for manufacturing monolithic composite structures comprising providing first and second subcomponents (1, 2) of composite material, attaching an expansion compensating tooling to the second subcomponent, placing the second subcomponent along with said tooling on the first subcomponent and bonding it to the latter by means of an uncured structural adhesive, covering the assembly comprising the first and second subcomponents and the tooling with a vacuum bag, performing an autoclave cycle for curing the curable material contained in said assembly under high temperature and pressure conditions, withdrawing said assembly from the curing autoclave and removing the expansion compensating tooling to obtain the desired monolithic composite structure. The tooling for carrying out the process comprises metal L- or I-shaped beams having a rough surface adapted to be applied to the second subcomponent. The invention is useful for manufacturing aircraft parts.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.