CAJ | 학술논문

建立了立式旋转试车台,研究了高过载对固体火箭发动机性能的影响.通过地面静止及不同过载(15gn,15gn;35gn,15gn)条件下点火对比试验,获得固体火箭发动机在不同过载条件下内弹道性能以及绝热层和喉衬的烧蚀规律.试验表明,随着过载增加,发动机压强增大、工作时间缩短;横向与轴向的组合过载恶化了烧蚀环境,使喉衬出现偏心烧蚀.
건립료입식선전시차태,연구료고과재대고체화전발동궤성능적영향.통과지면정지급불동과재(15gn,15gn;35gn,15gn)조건하점화대비시험,획득고체화전발동궤재불동과재조건하내탄도성능이급절열층화후츤적소식규률.시험표명,수착과재증가,발동궤압강증대、공작시간축단;횡향여축향적조합과재악화료소식배경,사후츤출현편심소식.
Experiments for effect on solid rocket motor (SRM) performance induced by overload were carried out on a vertical rotation test stand. The comparison of static tests and overload(15gn,15gn;35gn,15gn)firing tests was performed. The change of internal ballistics performance, insulator and throat insert abnormal erosion induced by overload were obtained from test. The results show that the increasing overload tends to raise the solid rocket pressure and shorten the work time. The lateral overload combined with the axial overload tends to deteriorate the insulation erosion environment and make the eccentric erosion of throat insert.