Rocket engine systems with an independently regulated cooling system

Abstract

An improved rocket engine system including a rocket engine, a coolant source, and a propellant source. Each of coolant source and propellant source is in operative communication with rocket engine whereby there is independent regulation or control of coolant source flow relative to propellant source flow. The improved rocket engine system may further include one or more of: at least one power source, at least one power source motor, at least one pump, at least one controller, and a propellant pressurizing source. The propellant source preferably includes a fuel source and an oxidizer source. An embodiment includes a cooling system with a coolant source, a fuel system with a fuel source, an oxidizer system with an oxidizer source, a propellant pressurizing system with a propellant pressurizing source, multiple pumps, an assembly of power source and controller, and a main rocket engine assembly.

What is claimed is: 
     
         1 . An improved rocket engine system comprising:
 a rocket engine;   a coolant source; and   a propellant source, wherein each of said coolant source and said propellant source is in operative communication with said rocket engine whereby there is independent regulation or control of the flow of said coolant source relative to the flow of said propellant source.   
     
     
         2 . The improved rocket engine system according to  claim 1 , wherein said coolant source is consumable and adds to the energy of combustion or mass flow. 
     
     
         3 . The improved rocket engine system according to  claim 1 , wherein said rocket engine is an electrically pumped rocket engine providing a broad range of fluid pumping conditions to meet throttling and performance requirements. 
     
     
         4 . The improved rocket engine system according to  claim 1 , further comprising at least one power source and at least one power source motor. 
     
     
         5 . The improved rocket engine system according to  claim 1 , further comprising at least one pump. 
     
     
         6 . The improved rocket engine system according to  claim 1 , further comprising at least one controller. 
     
     
         7 . The improved rocket engine system according to  claim 1 , further comprising a propellant pressurizing source. 
     
     
         8 . The improved rocket engine system according to  claim 1 , further comprising a lobed nozzle. 
     
     
         9 . The improved rocket engine system according to  claim 1 , further comprising a dual sleeve pintle injector adapted for allowing a plurality of propellant combinations to be used as primary oxidizer or fuel. 
     
     
         10 . The improved rocket engine system according to  claim 1 , further comprising at least one power source, at least one power source motor, at least one pump, at least one controller, and a propellant pressurizing source. 
     
     
         11 . The improved rocket engine system according to  claim 10 , wherein said coolant source is consumable and adds to the energy of combustion or mass flow. 
     
     
         12 . The improved rocket engine system according to  claim 10 , wherein said rocket engine is an electrically pumped rocket engine providing a broad range of fluid pumping conditions to meet throttling and performance requirements. 
     
     
         13 . The improved rocket engine system according to  claim 10 , further comprising a lobed nozzle. 
     
     
         14 . The improved rocket engine system according to  claim 10 , further comprising a dual sleeve pintle injector adapted for allowing a plurality of propellant combinations to be used as primary oxidizer or fuel. 
     
     
         15 . The improved rocket engine system according to  claim 1 , further comprising at least one power source, at least one power source motor, at least one pump, at least one controller, a propellant pressurizing source, and a gas generator plus turbine assembly. 
     
     
         16 . The improved rocket engine system according to  claim 15 , wherein said coolant source is consumable and adds to the energy of combustion or mass flow. 
     
     
         17 . The improved rocket engine system according to  claim 15 , wherein said rocket engine is an electrically pumped rocket engine providing a broad range of fluid pumping conditions to meet throttling and performance requirements. 
     
     
         18 . The improved rocket engine system according to  claim 15 , further comprising a lobed nozzle. 
     
     
         19 . The improved rocket engine system according to  claim 15 , further comprising a dual sleeve pintle injector adapted for allowing a plurality of propellant combinations to be used as primary oxidizer or fuel. 
     
     
         20 . The improved rocket engine system according to  claim 10 , wherein said improved rocket engine system is attached to a vehicle intended to exploit a positive lift to drag ratio while operating in sensible atmosphere where energy sources are ejected in flight to adjust vehicle performance or weight and balance. 
     
     
         21 . The improved rocket engine system according to  claim 1 , wherein said coolant source is diverted to an auxiliary thruster to provide ullage forces or altitude control. 
     
     
         22 . The improved rocket engine system according to  claim 1 , wherein said improved rocket engine system is attached to a rocket stage. 
     
     
         23 . The improved rocket engine system according to  claim 1 , wherein said improved rocket engine system is attached to a planetary lander or reusable launch vehicle. 
     
     
         24 . The improved rocket engine system according to  claim 1 , wherein at least one combination of said propellant source is changed in flight to improve system performance. 
     
     
         25 . The improved rocket engine system according to  claim 1 , wherein said improved rocket engine system is attached to a vehicle to provide motive force.