Inlet system for supersonic or hypersonic aircraft

US5116251A · kind A · utility

Assignee

• Messerschmitt Bolkow Blohm GmbH · DE

Inventors

• Bartholomäus Bichler · Raubling, DE
• Michael Jost · Unterschleißheim, DE

Key dates

• Filing date: Mar 18, 1991
• Grant date: May 26, 1992
• Expiry date: Mar 18, 2011

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y10T137/0536
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

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.