Method of making composite aircraft wing
Patent 4565595 Issued on January 21, 1986. Estimated Expiration Date: 
June 6, 2003. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
June 6, 2003. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 2754915 3641230 3771748 3910531 Multi-chambered cellular structure and method for manufacture Composite airfoil construction Single stage hot bonding method for producing composite honeycomb core structures Hybrid composite structures Composite structural skin spar joint and method of making Patent #: 4395450 InventorAssigneeApplicationNo. 06/514283 filed on 06/06/1983US Classes:156/156, With fluid pressure to prevent collapse of hollow structure during assembly and/or joining156/172, Winding about and uniting to core156/182, Of at least two bonded subassemblies156/245, In configured mold244/123.13, Honeycomb in skin panels244/123.3, Integral frame and skin264/258Joining a plurality of superposed fibrous or textile layersExaminersPrimary: Ball, Michael W.Attorney, Agent or FirmInternational ClassesB29C 70/08 (20060101)B29C 70/04 (20060101) B29C 70/10 (20060101) B29D 24/00 (20060101) B29C 70/24 (20060101) B29C 70/50 (20060101) B29D 31/00 (20060101) B64C 1/06 (20060101) B64C 1/00 (20060101) B64C 3/18 (20060101) B64C 3/00 (20060101) B29C 53/58 (20060101) B29C 53/00 (20060101) AbstractA pair of specially reinforced skin-spar joints in combination with a honeycomb core are used to build up a wing spar for a composite airplane wing. A series of contoured mandrels with a covering of fuel resistant material and a wrapped reinforced plastic are aligned one above the other. The wing spar materials are placed between the mandrels, honeycomb core is located alongside as well as wing skins to form a wing buildup. The buildup is placed in a mold, pressure applied to each mandrel forcing all the parts together, and the buildup heated to cure the resins and form a composite wing structure.Field of SearchOf at least two bonded subassembliesIn configured mold With fluid pressure to prevent collapse of hollow structure during assembly and/or joining Winding about and uniting to core With covering of discrete laminae with additional lamina Joining of nonplanar elements; e.g., configured hollow objects, etc. | |
