A method of reducing the visible flash caused from afterburning of a rocket motor by injecting a fire extinguishing a suppressant material into the exhaust gases from the rocket motor and injecting the fire extinguishing suppressant material near the exhaust end of the rocket motor nozzle and about an internal periphery of the exhaust nozzle. An effective fire extinguisher suppressant includes fluoro halogenated carbon compounds and specifically CBrF3. (Author)


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