| 摘要 |
Composite structures for producing articles include a core encapsulated in a somewhat rigid material. Both the core and encapsulating material can comprise a temperature resistant material to limit or substantially prevent degradation of the composite material when exposed to relatively high temperatures, such as those typically experienced during autoclave curing processes. The rigid material can be a wear resistance material that forms durable external surfaces. The core is made, in whole or in part, of carbon foam and the encapsulating material can be made, in whole or in part, of carbon fibers in a matrix. The composite structures can form a mandrel assembly for fabricating at least a portion of a fuselage of an aircraft. |
