关键词: 固体推进剂火箭发动机;推进剂燃速;内弹道计算;使用寿命

Abstract: or double base propellant,the experimentally measured values of burning rate reducewith storage or servile, so the chamber pressure and thrust of solid rocket motor(SRM)also reduce,which is call"degeneracy".For SRM with a regulating nozzle,the regulating of critical area A, dependson not only initial temperature Ti but also serviced years of grain. On the basis of ex-factory value Atothe reduce Ae can compensate completely "pressure degeneracy"and compensate basically"thrustdegeneracy"according to the number of service years and using the"pressure steadiness regulationmethod".

Key words: Soled propellant rocket motor;Propellant burning rate;Interior ballisticcalculation;Service life