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US 8,262,031 B2Granted
Co-flow jet aircraft
AssigneeUniversity of Miami
InventorsGecheng Zha, Sebastian Aspe, Joseph John Dussling, Nicholas Ramsay Heinz, Daniel J. Martinez
Life of this patent
Estimating the term…
Abstract
The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust.
Claims20
An aircraft, comprising:
- an aircraft body having a centerline defining a leading edge, a trailing edge, a first wing portion on one side of the centerline having a first wingtip and a second wing portion on the other side of the centerline having a second wingtip;
- an injection opening proximate the leading edge and extending across an aircraft body upper surface continuously from a location on the first wing portion to a location on the second wing portion;
- a recovery opening located between the injection opening and the trailing edge and extending across the aircraft body upper surface continuously from a location on the first wing portion to a location on the second wing portion;
- and
- one or more engine portions positioned between the recovery opening and the trailing edge.
2 more elements
An aircraft, comprising:
- an aircraft body having a centerline defining a leading edge, a trailing edge, a first wing portion on one side of the centerline having a first wingtip, a second wing portion on the other side of the centerline having a second wingtip, and an arcuate tail portion;
- an injection opening proximate the leading edge and extending across an aircraft body upper surface continuously from a location on the first wing portion to a location on the second wing portion;
- a recovery opening located between the injection opening and the trailing edge and extending across the aircraft body upper surface from a location on the first wing portion to a location on the second wing portion;
- and
- one or more engines at least partially integrated into the upper surface of the arcuate tail portion, wherein the recovery opening is in fluid communication with a fluid intake of the one or more engines.
2 more elements
Dependencies are inferred from the claim text.