Patent ID: 8960592
Filing Date: 2015-02-24
Classification: A63H,B64C,B64D

Abstract:
1. An aircraft comprising: a fuselage defining a first wing, a second wing, and a tail section; a compressor in said fuselage, said compressor defining an intake opening: a first fan and a second fan in said compressor; a drive shaft interconnecting said first fan and said second fan; a motor for rotating said drive shaft; a transmission in communication with said motor and said drive shaft for gearing up an output of said motor; a bypass duct for directing airflow to a location in front of said second fan; a plurality of nozzles for directing air flow out of said compressor in a selected one of a vertical or non-vertical direction; hover tubes extending from said compressor to adjust the aircraft in pitch, yaw and roll; wherein said compressor has a first chamber and a second chamber; said first fan is in said first chamber; said second fan in said second chamber; said first chamber and said second chamber interconnected via a selectively openable valve that remains open to regulate air flow from said first fan to said second fan; and said valve comprises an outer casing defining openings, an inner rotating member contained within said outer casing, said inner rotating member defining openings; wherein said inner rotating member may be selectively rotated to align said outer casing openings and said inner rotating member openings.