ROCKET ENGINE NOZZLE DESIGNED FOR ROTATING ROCKET RELATIVE TO LONGITUDINAL AXIS Russian patent published in 2003 - IPC

FIELD: rocketry. SUBSTANCE: proposed nozzle of rocket engine contains diverging supersonic part whose inner thermal protection is formed by spiral winding of reinforcement tape. Inner thermal protection of nozzle supersonic part contains reinforcement fiber, for instance, carbon or silica, and binder, for instance, phenol-formaldehyde resin. In process of ablation of binder, inner thermal protection forms spiral-like roughness of reinforcement fiber of height not less than 1/4 of thickness of laminar underlayer projecting into supersonic gas flow. EFFECT: provision of constant rotation of rocket during operation of engine without higher losses of specific impulse. 3 cl, 3 dwg