新型高燃速推进剂在固体发动机内燃烧特性研究  

Study on combustion properties of new high burning rate propellant in solid rocket motor

作　　者：郭效德[1] 李凤生[1] 宋洪昌[1] 刘冠鹏[1] 陈伟凡[1] 

机构地区：[1]南京理工大学国家特种超细粉体工程技术研究中心,南京210094

出　　处：《固体火箭技术》2007年第1期48-51,共4页Journal of Solid Rocket Technology

基　　金：总装预研项目(40406030401)

摘　　要：新型高燃速推进剂是一种采用小球粘结、无溶剂挤成型的复合改性双基推进剂,20℃、6.86MPa下用靶线法实测静态燃速为46.25mm/s。为研究这种新型高燃速推进剂在发动机内的燃烧特性,在不同燃通比和燃喉面积比的装药条件下,进行了发动机试验,获得了相应的压强-时间曲线。分析结果表明,该推进剂在火箭发动机内不同压强下可出现3种完全不同的燃烧类型,即类似于双基推进剂的平行层燃烧、类似于超高燃速推进剂的对流燃烧和有限对流燃烧,并给出了3种燃烧类型的判断条件。The new high burning rate propellant is a kind of modified composite double base propellant by binding small ball grain and extruding without solvent. The static burning rate of the propellant measured by the strand burner method is 46.25 mm/ s at 20 ℃ 6.86 MPa. In order to investigate combustion properties of the new propellant in rocket motor, motor test was carried out under different burning surface to port area ratio and different burning surface to throat area ratio, and corresponding p-t curves were obtained. The analysis results show that tho propellant in motor can present three totally different combustion types under different pressure, namely parallel-layer combustion which is similar to that of double base propellant, limited convection combustion and convection combustion which is similar to that of ultra-high burning rate propellant. Finally judgement criteria of three combustion types were given.

关 键 词：高燃速推进剂 平行层燃烧 对流燃烧 有限对流燃烧 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]