# US 2019/0315077 A1 · Method for forming stiffened composite parts > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0315077 A1 - Document ID: US20190315077A1 - Status: Published application - Kind: A1 - Application number: 16/461,243 - Filed: 2017-11-10 - Published: 2019-10-17 - Earliest claimed: 2016-11-16 - Assignees: GE Aviation Systems LLC - Applicants: GE Aviation Systems Limited - Inventors: Stephen Mason - Web page: https://patentgrep.com/patent/US20190315077A1 ## CPC - B29C 70/38: Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns {(application heads for tyres B29D30/28)} - B29C 70/382: {Automated fiber placement [AFP]} - B29C 70/545: {Perforating, cutting or machining during or after moulding} - B29L 2031/3076: {Aircrafts (blades, propellers B29L2031/08)} - Y02T 50/40: Weight reduction - B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00) - B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A method for forming a composite part includes providing a core (22), providing a set of fiber bands (24), placing the set of fiber bands (24) in a set of predetermined positions, and fixing the set of fiber bands (24) at the set of predetermined positions through the use of a binder material, such as resin. ## Claims ### Claim 1 A method for forming stiffened composite parts, the method comprising: cutting off relatively short fiber band pieces of a first length from a spread fiber band; placing the relatively short fiber band pieces at a set of predetermined positions on the core; and fixing the relatively short fiber band pieces at the set of predetermined positions through use of a binder material. ### Claim 2 (depends on 1) The method of claim 1, further including placing relatively long fiber band pieces of a second length prior to providing the core, wherein the first length is shorter than the second length. ### Claim 3 (depends on 2) The method of claim 2, further including providing the core on the relatively long fiber band pieces, and wherein the placing the relatively short fiber band pieces includes placing the relatively short fiber band pieces on the core opposite of the relatively long fiber band pieces. ### Claim 4 (depends on 3) The method of claim 3, wherein the placing the relatively short fiber band pieces including placing relatively short fiber band pieces that have at least one of a length dimension or width dimension shorter than a width dimension of the relatively long fiber band pieces. ### Claim 5 (depends on 1) The method of claim 1 further including providing a composite part frame. ### Claim 6 (depends on 5) The method of claim 5, wherein the providing the core includes providing the core to the composite part frame, and wherein the placing the relatively short fiber band pieces include placing the relatively short fiber band pieces at a set of predetermined positions relative to the frame. ### Claim 7 (depends on 5) The method of claim 5, further including placing multiple layers of the relatively short fiber band pieces at predetermined positions of the composite part frame. ### Claim 8 (depends on 1) The method of claim 1 wherein placing the relatively short fiber band pieces includes placing the relatively short fiber band pieces at a set of predetermined positions by way of an automated arm assembly. ### Claim 9 (depends on 8) The method of claim 8, wherein the cutting off relatively short fiber band pieces includes cutting off relatively short fiber band pieces by way of the automated arm assembly. ### Claim 10 (depends on 1) The method of claim 1, further including trimming a portion of the stiffened composite parts based on a template. ### Claim 11 (depends on 1) The method of claim 1 wherein the stiffened composite parts are avionics parts. ### Claim 12 (depends on 1) The method of claim 1 wherein the fixing the relatively short fiber band pieces includes fixing the relatively short fiber band pieces at the set of predetermined positions through use of a resin binder material. ### Claim 13 A method of forming a composite panel assembly, the method comprising: disposing a first layer of long fiber band pieces at a first set of predetermined positions; disposing a core adjacent to the first layer; disposing a second layer of short fiber band pieces at a second set of predetermined positions adjacent to the core, wherein the short fiber band pieces are shorter than the long fiber band pieces; and fixing the first layer and the second layer through the use of a binder material. ### Claim 14 (depends on 13) The method of claim 13, wherein disposing the second layer includes disposing a second layer of short fiber band pieces, wherein the short fiber band pieces are selected to include at least one of a length dimension or width dimension shorter than a width dimension of the long fiber band pieces. ### Claim 15 (depends on 14) The method of claim 14, further including providing a composite panel frame. ### Claim 16 (depends on 15) The method of claim 15, disposing the first layer includes disposing the first layer onto the composite part frame. ### Claim 17 (depends on 15) The method of claim 15 wherein disposing the second layer includes disposing multiple overlapping layer of the short fiber band pieces at a portion of the composite panel assembly overlapping the composite panel frame but not overlapping the core. ### Claim 18 (depends on 14) The method of claim 14 wherein at least one of disposing the first layer or disposing the second layer includes disposing by way of an automated arm assembly. ### Claim 19 (depends on 18) The method of claim 18, wherein the at least one of disposing the first layer or disposing the second layer includes cutting the fiber band pieces by way of the automated arm assembly. ### Claim 20 (depends on 13) The method of claim 13, further including trimming a portion of the composite panel assembly based on a template.