发明名称 |
INLET SYSTEM FOR SUPERSONIC OR HYPERSONIC AIRCRAFT |
摘要 |
An inlet system, which can be used for all supersonic or hypersonic engine inlets, comprises two or several separate parallel ducts which must be switched over in specific phases of flight. This is accomplished with a duct shaped parallel inlet element pivotably assigned to the inlet ramp of the inlet, which as a channel-connecting re-direction member alternately can close off the turbojet inlet duct as well as also the ramjet inlet. Preferably, the construction comprises a plurality of pivotably connected box-like elements interconnected in a movable manner.
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申请公布号 |
US5116251(A) |
申请公布日期 |
1992.05.26 |
申请号 |
US19910671121 |
申请日期 |
1991.03.18 |
申请人 |
MESSERSCHMITT-BOLKOW-BLOHN GMBH |
发明人 |
BICHLER, BARTHOLOMAEUS;JOST, MICHAEL |
分类号 |
B64D33/02;F02C7/042 |
主分类号 |
B64D33/02 |
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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