초록

This patent concerns VTOL propulsion systems that develop a forward flow of air through the air intake duct(s), by the methods of a internal duct system, reversing the rotation of the fan, or a variable pitch (thrust reversing) fan.

대표청구항 ▼

1. A vertical takeoff and landing propulsion system for a aircraft comprising:a) a main tubular duct, and b) a fan disposed within said main tubular duct, and c) means for rotating said fan whereby a airflow is created in said main tubular duct, and d) at least one tubular air intake duct having a f

1. A vertical takeoff and landing propulsion system for a aircraft comprising:a) a main tubular duct, and b) a fan disposed within said main tubular duct, and c) means for rotating said fan whereby a airflow is created in said main tubular duct, and d) at least one tubular air intake duct having a first end connecting to the forward part of said main tubular duct and a second end at about the forward part of said aircraft e) at least one tubular exhaust duct having first end connected to the aft part of said main tubular duct and a second end at about the aft part of said aircraft, and f) at least one air intake port located on top of said main tubular duct, and g) means for opening said air intake port during vertical takeoff and landing mode of operation and closing said air intake port during forward flight mode of operation, and h) the rotation of said fan causing the air flow to move forward in the air intake duct during the vertical takeoff and landing mode of operation, and aft towards the exhaust duct during the forward flight mode of operation, and i) means for turning downward said forward airflow at the forward end of said air intake duct during vertical takeoff and landing mode of operation, and j) means for turning downward an aft flow in the exhaust duct during vertical takeoff and landing. 2. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein said means for turning the aft flow in the exhaust duct downward during vertical takeoff and landing is further including:a) a exhaust duct nozzle at said second end of said exhaust duct, and b) a three bearing swivel exhaust duct that rotates to point said exhaust duct nozzle aft during forward flight, and rotates to point said exhaust duct nozzle downward during vertical takeoff and landing. 3. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein said means for turning the aft flow in the exhaust duct downward during the vertical takeoff and landing mode of operation is further including:a) at least one port on the bottom of said exhaust duct, and b) means for opening said port on the bottom of said exhaust duct during the vertical takeoff and landing mode of operation, and for closed said port on the bottom of said exhaust duct during the forward flight mode of operation, and c) means for closing said exhaust duct at a position aft of said port on the bottom of said exhaust duct, during the vertical takeoff and landing mode of operation, and for opening said exhaust duct during forward flight mode of operation, whereby the flow out of said second end of said exhaust duct is blocked during the vertical takeoff and landing mode of operation, and flow out said second end of said exhaust duct is allowed during forward flight mode of operation. 4. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 3 wherein said means for closing off said exhaust duct aft of said port on the bottom of said exhaust duct, during the vertical takeoff and landing mode of operation, is further including:a) a exhaust duct nozzle located at said second end of said exhaust duct, and b) means for closing said exhaust nozzle during vertical takeoff and landing mode of operation and opening said exhaust nozzle during the forward flight mode of operation. 5. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein the means for turning the aft flow in the exhaust duct downward during vertical takeoff and landing mode of operation is further including:a) at lease two rotational nozzles one located on each side of said exhaust duct, and b) means for rotating said rotational nozzles downward in the vertical takeoff and landing mode of operation, and aft in the forward flight mode of operation. 6. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein means for turning the aft flow in the exhaust duct downward during the vertical takeoff and landing mode is further including:a) at least two rotational nozzles one located on each side of said exhaust duct, and b) means for opening said rotational nozzles on the sides of said exhaust duct during the vertical takeoff and landing mode of operation and for closing said rotational nozzles during the forward flight mode of operation, and c) means for rotating said rotational nozzles, on the sides of said exhaust duct, downward during the vertical takeoff and landing mode of operation and rotating said rotational nozzles aft during the forward flight mode of operation, and d) means for closing said exhaust duct at a position aft of said rotational nozzles on each side of said exhaust duct, during the vertical takeoff and landing mode of operation, and for opening said exhaust duct during forward flight mode of operation, whereby the flow out of said second end of said exhaust duct is blocked during the vertical takeoff and landing mode of operation, and flow out said second end of said exhaust duct is allowed during forward flight mode of operation. 7. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein the means for turning the forward airflow in the air intake duct downward during the vertical takeoff and landing mode of operation is further including:a) a port on the bottom of said air intake duct, and b) means for opening said port on the bottom of said air intake duct during vertical takeoff and landing mode of operation, and closing said port on the bottom of said air intake duct during forward flight mode of operation, and c) means for closing said forward directed second end of said air intake duct during the vertical takeoff and landing mode of operation, and opening said second end of said air intake duct during forward flight mode of operation. 8. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein the means for turning the forward airflow in the air intake duct downward during the vertical takeoff and landing mode is further including:a) at least two rotational nozzles that form said second opening of said air intake duct, said rotational nozzles are located on the sides of said air intake duct, and b) means for rotating said rotational nozzles downward during the vertical takeoff and land mode of operation, and for rotating said rotational nozzles forward during the forward flight mode of operation. 9. The vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein the means for rotating said fan is a gas turbine engine.10. The vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein the means for rotating said fan is a internal combustion engine.11. The vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein said air intake port on the top of said main tubular duct is located backward of said fan within said main tubular duct.12. The vertical takeoff and landing propulsion system for a aircraft of claim 1 wherein:a) said fan is a variable pitch fan, and b) said air intake port on the top of said main tubular duct is located aft of said variable pitch fan, within said main tubular duct. 13. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 12 further comprising means for varying the pitch of the blades of said variable pitch fan, so that said variable pitch fan drives air forward during vertical takeoff and landing mode of operation, and drives air aft during forward flight mode of operation.14. The aircraft vertical takeoff and landing propulsion system for a aircraft of claim 12 wherein said means for rotating said fan is a gas turbine engine.15. The vertical takeoff and landing propulsion system for a aircraft of claim 12 wherein said means for rotating said fan is a internal combustion engine.16. The vertical takeoff and landing propulsion system for a aircraft of claim 12 further including:a) a second fan disposed within said main tubular duct that is located aft of the said variable pitch fan, and b) means for rotating said second fan. 17. The vertical takeoff and landing propulsion system for a aircraft of claim 16 wherein said air intake port on top of said main tubular air intake duct is located between said forward variable pitch fan and said second fan.18. The vertical takeoff and landing propulsion system for a aircraft of claim 1 further including means for rotating said fan clockwise, during one mode of operation, and counter clockwise, during the other mode of operation, so that said fan moves air forward into the air intake duct during vertical takeoff and landing mode of operation and aft into the exhaust duct during forward flight mode of operation.19. The vertical takeoff and landing propulsion system for a aircraft of claim 18 wherein said air intake port on top of said main tubular duct is located aft of said fan within said main tubular duct.20. The vertical takeoff and landing propulsion system for a aircraft of claim 18 further including:a) a second fan disposed within said main tubular duct that is located aft of said fan, and b) means for rotating said second fan. 21. The vertical takeoff and landing propulsion system for a aircraft of claim 20 wherein the said air intake port on top of said main tubular duct is located between said fan and said second fan.