Although this engine is a liquid-propellant rocket, it substitutes a
series of small combustion chambers and nozzles for the traditional
single large chamber and nozzle to achieve additional thrust. This
innovative combustion system features chambers and nozzles mounted on an
annular ring at the base of the engine. Thrust is derived from the
expansion of the exhaust gases against a large segmented plug in the
center of the engine. Flight control is achieved by varying the amount
of propellant introduced into the individual chamber sections. The
engine on exhibit burned liquid oxygen and kerosene to provide a thrust
of 22,680 kilograms (50,000 pounds).
The plug-nose rocket engine was developed at the General Electric
Company’s Malta Test Station in 1961.
The engine on exhibit is from the New York State Atomic and Space
Authority.