초록

A composite cycle rocket engine having an inner engine disposed to discharge directly into the nozzle of an outer engine, is described herein.

대표청구항 ▼

A composite rocket engine comprising: a first engine having a combustion chamber, throat section, and expansion nozzle; and a second engine, also having a combustion chamber, throat section, and expansion nozzle positioned such that at least a portion of said second engine is disposed within said fi

A composite rocket engine comprising: a first engine having a combustion chamber, throat section, and expansion nozzle; and a second engine, also having a combustion chamber, throat section, and expansion nozzle positioned such that at least a portion of said second engine is disposed within said first engine, wherein: said second engine traverses the throat section of said first engine so that the throat sections of the two engines function in parallel when said first and second engines operate together; the expansion nozzle of said second engine terminates within the expansion nozzle of said first engine proximate the throat section of said first engine to minimize weight of the composite engine; and the expansion nozzle of said first engine is shaped to complete expansion of gases from said second engine and provide said second engine with an effective area ratio when operated alone equal to the maximum cross-sectional area of said expansion nozzle of said first engine divided by the cross-sectional area of said throat section of said second engine.