Patent ID: 6360993
Filing Date: 2002-03-26
Classification: B64G,F02K

Abstract:
A low cost expendable self-contained single-stage only to orbit launch vehicle from which no solid vehicle component of substantial size is separated from the vehicle as the vehicle ascends from liftoff to orbit, the vehicle having a moderate reliability in the range of about 0.5 to about 0.8 for launching a payload of consumable items to low earth orbit to supply a space station or satellite, said launch vehicle comprising:a pressure-fed rocket engine for propelling said launch vehicle without use of turbomachinery; a nozzle mounted on said rocket engine having a fixed orientation relative to said launch vehicle for aiming products of combustion therefrom in a direction away from said launch vehicle; a fuel tank containing fuel for delivery to said rocket engine; an oxidizer tank containing oxidizer for delivery to said rocket engine; a pressurant tank containing an inert pressurant gas under pressure; a first conduit system for introducing the inert pressurant gas from said pressurant tank to said fuel tank; a second conduit system for introducing the inert pressurant gas from said pressurant tank to said oxidizer tank; a third conduit system for introducing the fuel from said fuel tank to said rocket engine; and a fourth conduit system for introducing the oxidizer from said oxidizer tank to said rocket engine for combustion with the and wherein the initial pressure in said pressurant tank is maintained at a level in excess of about 100 bar; wherein the initial pressure in each of said fuel tank and said oxidizer tank is maintained at a level in the range of about 8.5 to 20.0 bar; and wherein the initial pressure in said rocket engine is maintained at a level in the range of about 5 to 10 bar.