发明名称 |
Aircraft pressure containment assembly module |
摘要 |
An aircraft pressure containment module is adapted to be mounted generally transversely within an aircraft fuselage for providing pressure containment to separate pressurized and non-pressurized sections of an aircraft. A plurality of web segments are joined together to form a web member. A ring member is arranged on a first pressurized side of the web member. A plurality of truss assemblies are also arranged on the first side of the web member. Each truss assembly is comprised of a first truss member adapted to extend outwardly from the ring member to a peripheral edge of the web member. The first truss member is joined to the web member and joins together adjacent web segments. A second truss member extends from the first truss member in a direction generally normal to the first side of the web member. The second truss member is adapted to be joined to an aircraft fuselage in a longitudinal sense or it may comprise a portion of longitudinally extending member of the fuselage such as a stringer. A third truss member is joined to the second truss member and the first truss member to form a truss assembly having at least in part a generally triangular shape. The truss assemblies are adapted to react pressure loading from the web member to the fuselage of an aircraft in a manner similar to a conventional dome type pressure containment module. An aircraft using the module has an elongated fuselage extending in a longitudinal direction and the pressure containment module mounted generally transversely within the fuselage.
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申请公布号 |
US5899412(A) |
申请公布日期 |
1999.05.04 |
申请号 |
US19970995124 |
申请日期 |
1997.12.19 |
申请人 |
NORTHROP GRUMMAN CORPORATION |
发明人 |
DIIORIO, GEORGE D.;GRUBE, KENNETH P.;REINHARDT, MICHAEL H. |
分类号 |
B64C1/10;(IPC1-7):B64C1/10 |
主分类号 |
B64C1/10 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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