无喷管固体发动机装药技术研究  

AN INVESTIGATION OF CHARGING TECHNOLOGY FOR SOLID PROPELLANT OF NOZZLELESS ROCKET MOTORS

作　　者：汪志清[1] 

机构地区：[1]上海新风化工研究所

出　　处：《推进技术》1994年第3期56-61,共6页Journal of Propulsion Technology

摘　　要：为提高无喷管发动机的比冲，从装药角度研究了在低燃速推进剂配方中加入短纤维以提高推进剂的抗冲刷性能，采用装药＂喷管＂收敛段的倒锥形造型技术及两种不同燃速推进剂的同心层装药，使无喷管发动机的比冲稳定在１８８２．０～１９８９．０Ｎ·ｓ／ｋｇ，满足了预定要求。与有喷管同类型发动机的内弹道性能比较，无喷管发动机的总冲量达到相当高的水平。o improve specific impulse of nozzleless rocket motors, this paper has investigated the anti-erosion performance of low burning rate solid propellant mixed with short fibre, shaping technology of reversed cone nozzle in the contraction section of propellant 'nozzle' and concentric charging method of two solid propellants with various burning rates. The specific impulse of nozzleless rocket motorsis stabilized between 1882. 0～1989. 0 N· s/kg, which satisfies our requirement.The specific impulse of nozzleless rocket motors is extremely greater than that ofthe same rocket with nozzle.

关 键 词：无喷管 火箭发动机 固体推进剂 

分 类 号：V435.21[航空宇航科学与技术—航空宇航推进理论与工程]