| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a composite structural member and an aircraft fuselage that eliminate circumferential splices (joining plates) of the fuselage, eliminate keel splice components, and provide concentrated stiffness and strength where needed, to thereby decrease aircraft weight and simplify fuselage assembly. <P>SOLUTION: This disclosure is directed to a boron reinforced composite structural member 200. The concepts and technologies illustrated in this disclosure are taught within the context of a boron reinforced aircraft keel. The boron reinforced composite structural member 200 may be constructed of a structural member core 208 and a surrounding structural member casing 212. The structural member core 208 includes alternating layers of boron fiber reinforced plies 202 and layers of interior carbon fiber reinforced plies 204. The boron fiber reinforced plies 202 are oriented in a longitudinal direction, and the interior carbon fiber reinforced plies 204 are oriented diagonally, perpendicular, and parallel to the boron fiber reinforced plies 202. The structural member casing 212 includes layers of exterior carbon fiber reinforced plies 204 that substantially surround the structural member core 208. <P>COPYRIGHT: (C)2013,JPO&INPIT |
