Inlet system for supersonic or hypersonic aircraft

Details Inlet system for supersonic or hypersonic aircraft Inlet system for supersonic or hypersonic aircraft

1991-03-18

1992-05-26

Barefoot, Galen

Aeronautics and astronautics

Aircraft power plants

137 151, 602701, B64D 3302

Patent

active

051162512

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.

REFERENCES:
patent: 3161379 (1964-12-01), Lane
patent: 3295555 (1967-01-01), James et al.
patent: 3324660 (1967-06-01), Lane et al.
patent: 3358457 (1967-12-01), Caldwell et al.
patent: 3589379 (1971-06-01), Danes et al.
patent: 4121606 (1978-10-01), Holland et al.
patent: 4919364 (1990-04-01), John et al.

Affiliated with

Also associated with

Rating

Inlet system for supersonic or hypersonic aircraft does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Inlet system for supersonic or hypersonic aircraft, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Inlet system for supersonic or hypersonic aircraft will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-415912