固体发动机后效对导弹分离性能的影响分析
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摘要
对固体火箭发动机后效推力进行了分析和计算。采用经典流体力学发动机内弹道计算理论,运用等熵膨胀条件所得的燃烧室压强变化模型,预测发动机超临界压强后效冲量变化规律,给出临界压强以下的后效冲量预测模型。更精确地获取固体发动机后效对导弹分离前后的冲量影响,明确导弹分离的一些基本参数要求,确定固体发动机结束工作后所需的分离速度。
Post-thrust of a solid rocket motor is analyzed and calculated. The classic fluid mechanics theory of the motor's internal ballistics and the pressure variety model of combustor under the situation of isentropic process are used to predict the variety regulation of the cutoff impulse on the condition of supercritical pressure and to get the predict model of the cutoff impulse on the condition that the motor pressure is lower than the critical pressure. The impact of post-thrust of the solid rocket motor on the impulse foreand-aft the missile separation is obtained more accurately. Some basic parameter about missile separates is confirmed. The needed separate speed after the solid rocket motor work ends is determined.
Post-thrust of a solid rocket motor is analyzed and calculated. The classic fluid mechanics theory of the motor's internal ballistics and the pressure variety model of combustor under the situation of isentropic process are used to predict the variety regulation of the cutoff impulse on the condition of supercritical pressure and to get the predict model of the cutoff impulse on the condition that the motor pressure is lower than the critical pressure. The impact of post-thrust of the solid rocket motor on the impulse foreand-aft the missile separation is obtained more accurately. Some basic parameter about missile separates is confirmed. The needed separate speed after the solid rocket motor work ends is determined.
引文
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[11]Howasl C Rodean.Rockel Thrust Termination Transients[J].ARS Journal,1959,29(6):406-409.
[12]苏金明,阮沈勇.MATLAB实用指南[M].北京:电子工业出版社,2002.SU Jin-ming,RUAN Shen-yong.MATLAB Practical Guide[M].Beijing:Publishing House of Electronics Industry,2002.
[2]金其明.防空导弹工程[M].北京:中国宇航出版社,2004.JIN Qi-ming.The Air Defense Missile Engineering[M].Beijing:China Astronautic Publishing House,2004.
[3]丁海河,候晓,陈林泉.固体火箭发动机后效推力计算[J].固体火箭技术,2004,27(4):1006-2793.DING Hai-he,HOU Xiao,CHEN Lin-quan.Post-Tnrust Calculation of Solid Rocket Motor[J].Joumal of Solid Rocket Technology,2004,27(4):1006-2793.
[4]睦英,胡克娴.固体火箭发动机[M].北京:北京理工大学出版社,1990.MU Ying,HU Ke-xian.Solid Rocket Motor[M].Beijing:Beijing University of Technology Press,1990.
[5]李宜敏,张中钦,赵元修.固体火箭发动机原理[M].北京:国防工业出版社,1985.LI Yi-min,ZHANG Zhong-qin,ZHAO Yuan-xiu.The Principle of Solid Rocket Motor[M].Beijing:National Defence Industry Press,1985.
[6]张平,孙维申,睦英.固体火箭发动机原理[M].北京:北京理工大学出版社,1996.ZHANG Ping,SUN Wei-shen,MU Ying.The Principle of Solid Rocket Motor[M].Beijing:Beijing University of Technology Press,1996.
[7]戴耀松,赵瑞湘.国外固体火箭发动机及推进剂的发展动向[R].西安:情报研究报告,1988:45-47.DAI Yao-song,ZHAO Rui-xiang.The Development of Solid Rocket Motor and Propellant Overseas[R].Xi'an:Information Research Report,1988.
[8]陈启智.化学火箭发动机的进展概况[C]∥CSAA P-89-190,北京:中国航空学会第二届动力年会,1989:477-481.CHEN Qi-zhi.The Survey of Chemical Rocket Motor[C]∥CSAA P-89-190,Beijing:the 2nd Power Session of China Aeronautical Academy,1989:477-481.
[9]张德雄.国外航天用固体火箭发动机评述[C]∥CSA PR 88-009,西安:航天与导弹动力装置联合会议,1988:45-50.ZHANG De-xiong.The Commentary to Foreign Aerospace Solid Rocket Motor[C]∥CSA PR 88-009,Xi'an:the United Convention of Aerospace and Missile Propulsion,1988:45-50.
[10]吴齐芬,陈伟芳.高温稀薄气体热化学非平衡流动的DSMC方法[M].长沙:国防科技大学出版社,2000.WU Qi-fen,CHEN Wei-fang.DSMC Method for Rarefied Gas at High Temperature Thermochemical Non-Equilibrium Flow[M].Changsha:National University of Defense Technology Press,2000.
[11]Howasl C Rodean.Rockel Thrust Termination Transients[J].ARS Journal,1959,29(6):406-409.
[12]苏金明,阮沈勇.MATLAB实用指南[M].北京:电子工业出版社,2002.SU Jin-ming,RUAN Shen-yong.MATLAB Practical Guide[M].Beijing:Publishing House of Electronics Industry,2002.