Supersonic Aerospace International, LLC

Supersonie Aerospace International, LLC

Howard Lee

John M Morgenstern

Alan E Arslan

Walter McRae Franklin, Iii

Brian Quayle

Robert S Cuccias

Hossein Aminpour

Ken Hajic

John Scarcello

A supersonic aircraft comprises a fuselage extending forward and aft, wings coupled to lateral sides of the fuselage, and canards coupled to lateral sides of the fuselage forward of the wings. The individual canards are configured to generate shocks that wrap around the fuselage and intersect with wing leading edges on opposing sides of the fuselage.

Canard position and dihedral for boom reduction and pitch/directional control

A supersonic aircraft comprises a wing, a fuselage, a plurality of fuel tanks contained within the wing and/or fuselage, and a fuel transfer system communicatively coupled to the plurality of fuel tanks and capable of transferring fuel among the plurality of fuel tanks. The aircraft further comprises at least one sensor capable of indicating a flight parameter and a controller. The controller is coupled to the one or more sensors and to the fuel transfer system. The controller can transfer fuel among the plurality of fuel tanks and adjust the aircraft center of gravity to reduce trim drag and increase aircraft range.

Aircraft with active center of gravity control

A supersonic aircraft comprises a wing having upper and lower surfaces and extending from a leading edge to a trailing edge and at least two engine nacelles coupled to the lower surface of the wing on the trailing edge. The supersonic aircraft further comprises an inverted V-tail abutting to the upper side of the wing comprising a central vertical stabilizer, at least two inverted stabilizers coupled to sides of the central vertical stabilizer and coupled to the wing and supporting at least two engine nacelles, and at least two ruddervators respectively pivotally coupled to at least two inverted stabilizers. The supersonic aircraft also comprises a controller coupled to at least two ruddervators and capable of adjusting the aircraft longitudinal lift distribution throughout a flight envelope to maintain a reduced sonic boom and reduced drag trim condition.

Aircraft tail configuration for sonic boom reduction

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Monterey Park, CA, United States of America

Howard Lee