Internal duct VTOL aircraft propulsion system

Abstract

This patent concerns a internal duct VTOL propulsion system. To establish balance in a hover lift is generated forward and aft in the aircraft center of gravity. Aft lift is developed by vectoring the aft flow of exhaust in the exhaust duct downward. Forward lift is developed by vectoring a forward air flow of air in the air intake duct downward. Using the air intake duct allows forward lift to be generated well forward of the aircraft's center of gravity. This reduces the forward thrust required to establish balance while in a hover. During VTOL air is drawn through the top of the aircraft. During forward flight air enter the air intake ducts. Internal ducts conduct air, moved aft by the fan, around the fan and forward into the air intake ducts during VTOL. The internal ducts are closed during forward flight.

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, and    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 in front of said fan deposed within 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 causes air to move aft towards the exhaust duct during the vertical takeoff and landing mode of operation and the forward flight mode of operation, and    i) means for turning downward an forward airflow at the forward end of said air intake duct during the vertical takeoff and landing mode of operation, and    j) means for turning downward an aft flow in said exhaust duct during the vertical takeoff and landing mode of operation, and    k) at least one tubular internal duct having a first end connected to the said tubular air intake duct, and a second end connected to said main tubular duct, at a location aft of said fan disposed Within said main tubular duct, and    l) means for opening said internal air ducts to allow a forward airflow during the vertical takeoff and landing mode of operation, and for closing said internal air ducts and preventing a airflow during the forward flight mode of operation, and    m) means for opening to allow a aft airflow from said tubular air intake duct into said main tubular duct during forward flight, and for closing to prevent a airflow from said tubular air intake duct into said main tubular duct during the vertical takeoff and landing mode of operation.    
   
   
       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 dosing 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, hereby 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 pipe 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 flaw 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 the 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 flown 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 located on opposite sides of said air intake duct that form said second opening 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 said first 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 said first means for rotating said fan is a Internal combustion engine.