ROCKET VEHICLE THRUST AUGMENTATION WITHIN DIVERGENT SECTION OF NOZZLE

摘要

Augmentation of the thrust achieved by a supersonic nozzle (11) of continuous curvature is achieved by causing secondary combustion to occur in an annular region (25) of the combustion that complements the primary combustion gas (26) passing through the nozzle and maintains a wall pressure that is greater or equal to the ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.