High-speed-launch ramjet booster

Abstract

A high-speed-launch ramjet boost (HSLRB) engine includes a combustion system for igniting fuel pumped by a fuel pump from a fuel tank, where the combustion system includes an igniter, fuel injectors and frame holders. An inlet provides a pathway for air to flow toward the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator is included for exhausting exhaust gas from combustion of the fuel by the combustion system. A processor is coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein the processor provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle.

1 . A high-speed-launch ramjet boost (HSLRB) engine, comprising:
 A combustion system for igniting fuel pumped by a fuel pump from a fuel tank, said combustion system comprising an igniter, fuel injectors and frame holders;   at least one inlet providing an pathway for air to flow toward said fuel injectors;   a variable geometry (VG) nozzle having a nozzle actuator for exhausting exhaust gas from combustion of said fuel by said combustion system, and   a processor coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein said processor provides control signals to said nozzle actuator for dynamically controlling an aperture size of said VG nozzle.   
     
     
         2 . The HSLRB engine of  claim 1 , wherein said inlet comprises a VG inlet having an inlet actuator, and said processor provides control signals to said inlet actuator for dynamically controlling a geometry of said VG inlet. 
     
     
         3 . The HSLRB engine of  claim 2 , wherein said VG inlet includes an inlet cover. 
     
     
         4 . A launch vehicle, comprising:
 a high-speed-launch ramjet boost (HSLRB) stage including:   a frame including a front portion and an aft portion, and a fuel tank and fuel pump within said frame;   a high-speed-launch ramjet boost (HSLRB) engine within said frame including:
 a combustion system for igniting fuel pumped by said fuel pump from said fuel tank, said combustion system comprising an igniter, fuel injectors and frame holders; 
 at least one inlet providing an pathway for air to flow within said frame toward said fuel injectors; 
 a variable geometry (VG) nozzle having a nozzle actuator at said aft portion for exhausting exhaust gas from combustion of said fuel by said combustion system, and 
 a processor coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein said processor provides control signals to said nozzle actuator for dynamically controlling a aperture size of said VG nozzle, and 
 at least one other stage including a payload attached to said aft portion of said HSLRB stage. 
   
     
     
         5 . The launch vehicle of  claim 4 , wherein said inlet comprises a VG inlet having an inlet actuator, and said processor provides control signals to said inlet actuator for dynamically controlling a geometry of said inlet. 
     
     
         6 . The launch vehicle of  claim 5 , wherein said VG inlet includes an inlet cover. 
     
     
         7 . A method of propulsion using a ramjet, comprising:
 providing a high-speed-launch ramjet boost (HSLRB) stage including a frame including a front portion and an aft portion, and a fuel tank and fuel pump within said frame and a high-speed-launch ramjet boost (HSLRB) engine within said frame attached to a high-speed launch aircraft which provides a speed of at least Mach 2.0; said HSLRB engine including:
 a combustion system for igniting fuel pumped by said fuel pump from said fuel tank, said combustion system comprising an igniter, fuel injectors and frame holders; 
 at least one inlet providing a pathway for air to flow within said frame toward said fuel injectors; 
 a variable geometry (VG) nozzle having a nozzle actuator at said aft portion for exhausting exhaust gas from combustion of said fuel by said combustion system, and 
 a processor coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein said processor provides control signals to said nozzle actuator for dynamically controlling an aperture size of said VG nozzle, 
   carrying said HSLRB stage to a speed of at least Mach 1.5 during flight of said high-speed launch aircraft;   igniting said HSLRB engine while attached to said high-speed launch aircraft when at a speed of at least 2.0 Mach, and   separating said HSLRB stage from said high-speed launch aircraft after said igniting.   
     
     
         8 . The method of  claim 7 , wherein said HSLRB engine generates sufficient excess thrust to separate from said high-speed launch aircraft and accelerate to a speed of at least 3 Mach more relative to its speed at a time of said separating. 
     
     
         9 . The method of  claim 7 , wherein said inlet comprises a VG inlet having an inlet actuator, and wherein said processor provides control signals to said inlet actuator for dynamically controlling a geometry of said VG inlet. 
     
     
         10 . The method of  claim 9 , wherein said VG inlet includes a frangible inlet cover, wherein said frangible inlet cover is shattered before said igniting. 
     
     
         11 . A high-speed-launch ramjet boost (HSLRB) engine, comprising:
 A combustion system for igniting fuel pumped by a fuel pump from a fuel tank, said combustion system comprising an igniter, fuel injectors and frame holders;   at least one variable geometry (VG) inlet having an inlet actuator providing a pathway for air to flow toward said fuel injectors;   a variable geometry (VG) nozzle having a nozzle actuator for exhausting exhaust gas from combustion of said fuel by said combustion system, and a processor coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein said processor provides control signals to said nozzle actuator for dynamically controlling an aperture size of said VG nozzle and said processor provides control signals to said inlet actuator for dynamically controlling a geometry of said VG inlet.   
     
     
         12 . The HSLRB engine of  claim 11 , wherein said VG inlet includes an inlet cover.