固体火箭发动机单室双推力装药设计
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摘要
以某型火箭弹为研究背景,从推进剂种类选择、推进剂药型分类探讨及火箭弹内弹道计算依次展开,借助Matlab软件编制程序研究单室双推力火箭发动机装药设计的影响因素。经过反复迭代计算,多组结果进行比较,最终确定装药几何结构参数。结果表明:所得到的内弹道计算曲线满足总体要求,与试验数据吻合较好,设计过程中得到的调整经验总结对固体火箭发动机的研制具有一定的参考价值。
Taking a certain type of rocket projectile as the research background,the influence factors of the grain design of the single chamber dual thrust rocket engine are studied by Matlab software from the selection of propellant type,the classification of propellant type and the calculation of the internal ballistics. After repeated calculations,the results of many groups are compared and the geometric parameters of the charge are finally determined. The results show that the calculated curve of the interior ballistics meets the overall requirements and is in good agreement with the test data of the range. The adjustment experience in the design process has a certain reference value for the development of solid rocket motor.
Taking a certain type of rocket projectile as the research background,the influence factors of the grain design of the single chamber dual thrust rocket engine are studied by Matlab software from the selection of propellant type,the classification of propellant type and the calculation of the internal ballistics. After repeated calculations,the results of many groups are compared and the geometric parameters of the charge are finally determined. The results show that the calculated curve of the interior ballistics meets the overall requirements and is in good agreement with the test data of the range. The adjustment experience in the design process has a certain reference value for the development of solid rocket motor.
引文
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[14]宋颜舒.固体火箭发动机单室双推力药柱燃烧规律研究[D].沈阳:沈阳理工大学,2016.
[15]柯彪,高跃飞,罗炳华,等.C#与Matlab混合编程在内弹道设计中的应用[J].弹箭与制导学报,2013,33(5):129-132.
[2]唐宏,何慧珠,陈国光.固体火箭发动机总体设计[J].中北大学学报(自然科学版),2012,33(3):251-256.
[3]龚建良,樊学忠,李宏岩,等.单室双推力发动机装药的瞬态结构完整性分析[J].弹箭与制导学报,2016,36(6):78-82.
[4]赵秀超,黄克超,周长省,等.火箭发动机单室双推力多孔装药设计方法[J].弹道学报,2006,18(4):45-47.
[5]周长省,鞠玉涛,朱福亚,等.火箭弹设计理论[M].北京:北京理工大学出版社,2005:10-47.
[6]董师颜,张兆良.固体火箭发动机原理[M].北京:北京理工大学出版社,1996.
[7]李祥琴.某火箭弹用单室双推力固体发动机研究[D].武汉:华中科技大学出版社,2014.
[8] CHYUAN S W. Nonlinear thermoviscoelastic analysis of solid propellant grains subjected to temperature loading[J]. Finite Elements in Analysis and Design,2002,38(7):613-630.
[9]朱卫兵.固体火箭发动机药柱结构完整性及可靠性分析:[D].哈尔滨:哈尔滨工程大学,2005.
[10]代志高,宋琴,吴京汉,等.单室双推力固体火箭发动机用NEPE低燃速推进剂的燃烧性能[J].固体火箭技术,2018,41(1):47-52.
[11]王恒生,张国军,程艳婷,等.固体推进剂中新型含能材料研究进展[J].化工科技,2012,20(1):76-80.
[12] CHYUAN S W.Dynamic analysis of solid propellant grains subjected to pressurization loading[J]. Jounal of Sound and Vibration,2003,268(3):465-483.
[13]田长华,谢五喜,王琳,等.浇铸单室双推固体推进剂界面力学性能研究[J].科学技术与工程,2015,15(22):153-156.
[14]宋颜舒.固体火箭发动机单室双推力药柱燃烧规律研究[D].沈阳:沈阳理工大学,2016.
[15]柯彪,高跃飞,罗炳华,等.C#与Matlab混合编程在内弹道设计中的应用[J].弹箭与制导学报,2013,33(5):129-132.