CAJ | 학술논문

为研究燃面变化对膏体火箭发动机内弹道调节精度的影响,根据膏体火箭发动机的工作原理,分别推导了直圆管喷嘴和锥形扩张喷嘴型面下的膏体推进剂燃面方程,建立了膏体火箭发动机零维内弹道模型,分析了喷嘴型面对发动机内弹道性能的影响,并进行了直圆管喷嘴发动机试验.结果表明,直圆管喷嘴下计算的点火时间比试验结果短,但平衡时间及平衡压强与试验结果基本吻合,喷嘴型面变化对发动机平衡时间影响很大.
위연구연면변화대고체화전발동궤내탄도조절정도적영향,근거고체화전발동궤적공작원리,분별추도료직원관분취화추형확장분취형면하적고체추진제연면방정,건립료고체화전발동궤령유내탄도모형,분석료분취형면대발동궤내탄도성능적영향,병진행료직원관분취발동궤시험.결과표명,직원관분취하계산적점화시간비시험결과단,단평형시간급평형압강여시험결과기본문합,분취형면변화대발동궤평형시간영향흔대.
In order to study effects of burning surface variation on interior ballistics adjustment precision of pasty propellant rocket motor, burning surface functions of straight round pipe nozzle and conical expand nozzle were derived respectively based on the working principle of pasty propellant rocket motor. A 0-dimensional interior ballistics model was built. The influence of nozzle profile on interior ballistic performance of pasty propellant rocket motor was analyzed. Engine test with straight round pipe nozzle was carried out. Results show that the computed ignition time of straight round pipe nozzle is shorter than test time, but balance time and balance pressure are in agreement with test results. Nozzle profile variation affects balance time greatly.