固体火箭发动机性能蜕变的压强补偿

PRESSURE COMPENSATION FOR PERFORMANCE DEGENERACY OF SOLID ROCKET MOTORS

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

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

摘要:

介绍了采用缩小喷管喉径的方法，对固体火箭发动机燃烧室压强和推力进行补偿，以达到延长发动机使用寿命的目的。

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".