一种固体火箭发动机的点火异常峰分析与改进
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摘要
本论文是以某固体火箭发动机静止试验压强曲线2.2s出现的异常峰值为研究背景,通过对该点火发动机和主发动机的内弹道数字仿真以及流场计算,展开对发动机点火异常的问题分析、故障定位、改进设计、改进验证试验。
本文的研究内容涵盖以下四部分:
为了判断某固体火箭发动机首次点火试验的内弹道压强曲线及性能是否正常,要求该发动机和点火发动机进行内弹道仿真。首先展开该点火发动机的设计方案,具体包括:点火发动机的总体参数设计、点火药柱的优化设计、点火发动机壳体的工程设计及有限元法强度校核、点火药盒的设计等;运用固体火箭发动机内弹道性能数字仿真软件,采用零维内弹道数学模型,得出该点火发动机内弹道仿真曲线。
然后对该发动机点火启动过程进行内弹道仿真,仍采用零维内弹道数学模型,运用固体火箭发动机内弹道性能数字仿真软件,将点火药柱燃气生成量叠加到主装药燃气生成量上;将主装药简化成二维燃烧,采用Fluent动网格技术,进行发动机瞬态内流场计算,得出某时刻的流场速度、压强、温度、马赫数结果,分析发动机中燃气工作过程及内弹道性能。
接着根据该发动机点火启动内弹道仿真结果,判定该发动机点火试验的内弹道曲线出现异常压强峰。经过分析排查,确定异常原因是喷管喉部被点火发动机未烧熔壳体堵塞引起的,影响发动机的点火可靠性,必须采取措施改进。
最后介绍了该发动机点火发动机的改进设计,主要是点火发动机壳体结构的优化,后续点火试验验证了改进措施有效。
至此,圆满完成某型固体火箭发动机的点火设计及优化。
通过对该发动机点火试验内弹道压强曲线异常的分析和点火发动机的优化设计,得出:一体化球头结构的点火发动机能有效地避免点火时未完全烧熔的球头堵塞喷管喉部而出现的压强骤升问题;该结构尤其适用于装药短、喉径小的固体火箭发动机,可广泛应用在大、中、小型发动机上,能有效提高发动机的点火可靠性。
Analyzing the anomalism peak appeared at 2.2 second on the pressure curve during a solid rocket motor being tested is taken as background in this paper. Through inner ballistic digital emulation and fluent calculation to the ignition motor and the main motor, we can analyze anomalism problem of the motor ignition test, determine failure, improve designation and do validation test.
There are four parts as below included in this report:
In order to judge whether a solid rocket motor inner ballistic pressure curve and performance is normal or not during first ignition test, it’s required to emulate inner ballistic of the motor and the ignition motor. At first, the ignition motor designation is developed, which includes: general parameters of ignition motor, optimization of ignition grain, experimental designation and finite member intension check of ignition motor shell, ignition case designation and etc. Applying solid rocket motor inner ballistic performance digital emulation software and Zero-Dimension inner ballistic mathematics model, we can get the ignition motor ballistic emulation curve.
Then inner ballistic of the motor ignition and start up is emulated, while still applying Zero-Dimension inner ballistic mathematics model and using solid rocket motor inner ballistic performance digital emulation software, and adding up the ignition grain gas to the main motor grain gas. Simplifying the main motor grain to Tow-Dimension burning, using Fluent motive grid technology, we can do motor instant inner flow calculation, get flow velocity, pressure, temperature and mach number at one time, and analyze motor work process and inner ballistic performance.
According to the inner ballistic emulation result of the motor ignition and start up, we judge that there is anomalism pressure peak in the motor ignition test ballistic curve. After analysis and exclusion, the reason is that the nozzle throat is jammed by not melt ignition motor shell. It will influence motor ignition reliability, we must improve it.
Finally improvements on this ignition motor are introduced, mainly about ignition motor shell optimization. Later validation test proves those are effective.
From now on, the solid rocket motor ignition designation is brought to success perfectly.
Through this study about design and optimization of ignition motor, we get: the integral global head ignition motor can effectively resolve the anomalous peak value of pressure because the nozzle throat is jammed by not melted global seal cover after ignition motor works, which is applicable in all kinds of solid rocket motors, especially those whose grain length is short and nozzle diameter is small, and improve ignition reliability.
本文的研究内容涵盖以下四部分:
为了判断某固体火箭发动机首次点火试验的内弹道压强曲线及性能是否正常,要求该发动机和点火发动机进行内弹道仿真。首先展开该点火发动机的设计方案,具体包括:点火发动机的总体参数设计、点火药柱的优化设计、点火发动机壳体的工程设计及有限元法强度校核、点火药盒的设计等;运用固体火箭发动机内弹道性能数字仿真软件,采用零维内弹道数学模型,得出该点火发动机内弹道仿真曲线。
然后对该发动机点火启动过程进行内弹道仿真,仍采用零维内弹道数学模型,运用固体火箭发动机内弹道性能数字仿真软件,将点火药柱燃气生成量叠加到主装药燃气生成量上;将主装药简化成二维燃烧,采用Fluent动网格技术,进行发动机瞬态内流场计算,得出某时刻的流场速度、压强、温度、马赫数结果,分析发动机中燃气工作过程及内弹道性能。
接着根据该发动机点火启动内弹道仿真结果,判定该发动机点火试验的内弹道曲线出现异常压强峰。经过分析排查,确定异常原因是喷管喉部被点火发动机未烧熔壳体堵塞引起的,影响发动机的点火可靠性,必须采取措施改进。
最后介绍了该发动机点火发动机的改进设计,主要是点火发动机壳体结构的优化,后续点火试验验证了改进措施有效。
至此,圆满完成某型固体火箭发动机的点火设计及优化。
通过对该发动机点火试验内弹道压强曲线异常的分析和点火发动机的优化设计,得出:一体化球头结构的点火发动机能有效地避免点火时未完全烧熔的球头堵塞喷管喉部而出现的压强骤升问题;该结构尤其适用于装药短、喉径小的固体火箭发动机,可广泛应用在大、中、小型发动机上,能有效提高发动机的点火可靠性。
Analyzing the anomalism peak appeared at 2.2 second on the pressure curve during a solid rocket motor being tested is taken as background in this paper. Through inner ballistic digital emulation and fluent calculation to the ignition motor and the main motor, we can analyze anomalism problem of the motor ignition test, determine failure, improve designation and do validation test.
There are four parts as below included in this report:
In order to judge whether a solid rocket motor inner ballistic pressure curve and performance is normal or not during first ignition test, it’s required to emulate inner ballistic of the motor and the ignition motor. At first, the ignition motor designation is developed, which includes: general parameters of ignition motor, optimization of ignition grain, experimental designation and finite member intension check of ignition motor shell, ignition case designation and etc. Applying solid rocket motor inner ballistic performance digital emulation software and Zero-Dimension inner ballistic mathematics model, we can get the ignition motor ballistic emulation curve.
Then inner ballistic of the motor ignition and start up is emulated, while still applying Zero-Dimension inner ballistic mathematics model and using solid rocket motor inner ballistic performance digital emulation software, and adding up the ignition grain gas to the main motor grain gas. Simplifying the main motor grain to Tow-Dimension burning, using Fluent motive grid technology, we can do motor instant inner flow calculation, get flow velocity, pressure, temperature and mach number at one time, and analyze motor work process and inner ballistic performance.
According to the inner ballistic emulation result of the motor ignition and start up, we judge that there is anomalism pressure peak in the motor ignition test ballistic curve. After analysis and exclusion, the reason is that the nozzle throat is jammed by not melt ignition motor shell. It will influence motor ignition reliability, we must improve it.
Finally improvements on this ignition motor are introduced, mainly about ignition motor shell optimization. Later validation test proves those are effective.
From now on, the solid rocket motor ignition designation is brought to success perfectly.
Through this study about design and optimization of ignition motor, we get: the integral global head ignition motor can effectively resolve the anomalous peak value of pressure because the nozzle throat is jammed by not melted global seal cover after ignition motor works, which is applicable in all kinds of solid rocket motors, especially those whose grain length is short and nozzle diameter is small, and improve ignition reliability.
引文
[1]邢继发等,《世界导弹与航天发动机大全》,军事科学出版社
[2]张平,《从SDI计划重点的转移看固体火箭推进技术的应用前景》,固体火箭推进技术学术会议论文集,1993
[3]王铮、胡永强等,《固体火箭发动机》,中国宇航出版社,1993
[4] Clyde E. Carr Jr., Barbara A. Leary. Solid rockets [J]. Aerospace America, 2010(12)
[5]张旭东,王宏伟,邢耀国等,《某固体火箭发动机点火启动过程的仿真研究》,海军航空工程学院学报,2006,21 (3)
[6]王有元等,《固体火箭发动机设计》,国防工业出版社,1984
[7]李宜敏、张中钦、张远君等,《固体火箭发动机原理》,1999
[8]董师颜、张兆良,《固体火箭发动机原理》,北京理工大学出版社,1996
[9]陈汝训等,《固体火箭发动机设计与研究》,中国宇航出版社,1991
[10]谢蔚民,吴心平.固体火箭发动机内弹道曲线异常现象的鉴别.推进技术, 1985, (2): 7-13
[11]张旭东,王宏伟,邢耀国等.某固体火箭发动机点火启动过程的仿真研究.海军航空工程学院学报, 2006, 21 (3): 319-321.
[12]余贞勇,甘晓松.小型固体发动机尾部药型对点火升压过程的影响.固体火箭技术, 2002, 25 (3): 21-25.
[13]郭凤美,陈步学,吴心平.固体火箭发动机内弹道异常现象的计算机辅助分析.固体火箭技术, 1989, (4): 13-20.
[14]田江桥,张斌兴,张伟青等.固体火箭发动机试验故障分析.上海航天, 2002, (4): 58-61.
[15]金伟娅,《可靠性工程》,北京:化学工业出版社,2005
[16]李进贤,《火箭发动机可靠性》,西北工业大学出版社
[17]北京理工大学一系固体火箭发动机原理[M]北京:北京理工大学出版社,1981
[18]方丁酉、张为华、杨涛等,《固体火箭发动机内弹道学[M]》,长沙:国防科技大学出版社,1997
[19]王磊等,《基于Pro/E软件进行固体火箭发动机内弹道计算的方法初探》,中国新技术新产品,2009年第10期
[20] Coats D E,Levine J N.A Computer Program Prediction of Solid Propellant Rocket Motor Performance Volume I [R],1975
[21]田维平等,《固体发动机药柱CAD及燃烧模型分析》,固体火箭技术,1993年第3期
[22] [俄]A?C?科罗捷耶夫等,《固体火箭发动机气体动力学与热物理过程》,2004
[23]侯林法,《复合固体推进剂》,中国宇航出版社,2005
[24]张书俊,《固体火箭发动机粘弹性药柱结构可靠性分析》,固体火箭技术,2006,29(3):183-187
[25]张书俊、任钧国、吴志桥,《固体火箭发动机药柱点火过程结构可靠性的响应面法》,固体火箭技术,2006,29(6):404-408
[26]潘奠华.固化降温过程中固体火箭发动机材料参数的影响分析[J].烟台大学学报(自然科学与工程版),2006(1):64-67
[27]韦世峰,温度和内压作用下装药结构完整性分析[D].西安:西北工业大学,2006:34.36
[28]蒙上阳.基于粘弹性有限元方法的固体火箭发动机结构完整性分析[D].长沙:国防科技大学,2005
[29]蔡峨,《粘弹性力学基础》,北京航空航天大学出版社
[30]郝松林,《粘弹性力学基础》,科学出版社,1983
[31] Graham.G.and Lee,The Correspondence Principle of Linear Viscoelasticity Theory for Mixed Boundary Value Problems Involving Time-dependent Boundary Regions,Quart.Appl.Math,26,1968
[32] Landel,R.F.and Smith,T.L.,Viscoelasticity Properties of Rubber Like Composite Propellants and Filled Elastomers,J.Am.Rocket Soc.,VOL.31,1961
[33] Parr,C.H.,Deformations and Stresses in Ces-bouded Solid Propellant Grains of Finite Length by Numerical Methods,AD 282055,1962
[34]颜庆津,《数值分析》,北京航空航天大学出版社,1999
[35]谭浩强,《C程序设计》,清华大学出版社,1999
[36]施吉林、刘淑珍、陈桂芝,《计算机数值方法》,高等教育出版社,2002
[37]王心明,《工程压力容器设计与计算》,国防工业出版社,1986
[38]范顺成等,《机械设计基础》,机械工业出版社,2007
[39]王先逵,《机械制造工艺学》,机械工业出版社,1995
[40]蒋友谅,《有限元法基础》,国防工业出版社,1980
[41] O.C.Zienkwich,《有限元法》,科学出版社
[42]谢贻权、何福保,弹性和塑性力学中的有限单元法,机械工业出版社,1982
[43]上海交通大学有限单元法翻译组译,结构和连续力学中的有限单元法,国防工业出版社,1973
[44]龚曙光,《ANSYS工程应用实例解析》,机械工业出版社,2003
[45] MSC.Software.PCL and customization[M].Los Angeles : The Macneal-Schwendler Corporation,2005
[46]隋允康、杜家政、彭细荣等,MSC.Nastran有限元动力分析与优化设计实用教程[M].北京:科学出版社,2004
[47] MSC.software.MSC.Patran user’s manual [M].Los Angeles:The Macneal-Schwendler Corporation,2005
[48]蒙上阳、唐国金、雷勇军等,Burgers模型的参数获取方法[J].固体火箭技术,2003,26(2)
[49] Biot,M.A.,Theory of Stress-Strain Relation in Anisotropic Viscpelasticity and Relaxation Phenomen,J.Appl.Phy.,Vol.25,1954
[50] Coleman,B.D.and Noll,W.,Foundation of Linear Viscoelasticity,Reviews of Modern Physics,Vol.33,1961
[51] Klaus-Jorgen Bathle,《Finite Element Procedures In Engineering Analysis》,Prentice-Hall Inc,1982
[52] Kyuichiro Washizu,《Variation Methods In Eleasticity And Plasticity》,Third Edition,Pergaman Press,1982
[53] Louis Komzsik,《MSC.Nastran 2001 Numerical Method User’s Guide》,MSC.Software
[54]张永昌,《MSC.Nastran有限元分析理论基础与应用》,科学出版社,2004
[55]成一、陈守文,《火工品点火药点火性能的研究》,1003-1480(2001)04-002102
[56] J.A康克林,《烟火化学—基本原理和理论[M]》,陕西秦兴烟火联合公司出版,1988
[57]晋东,《黑火药[M]》,国防工业出版社,1978
[58]王泽山等,《火药实验方法[M]》,兵器工业出版社,1996
[59]屠小昌、王建生,《固体火箭发动机点火药量的计算》,中国航天机电集团公司210所
[60]王光林、蔡峨等,《固体火箭发动机设计》,航空专业教材编审室
[61]石润章、李成忠,《固体火箭发动机点火过程分析》[J]海军航空工程学院学报,2001,16(4):475-477;
[62]屠小昌、王建生,《固体火箭发动机点火药量的计算》[J].固体火箭技术,2000,23(4):5-7;
[63]刘君、张为华、刘伟,《某型号固体火箭发动机点火过程的数值模拟》[J].固体火箭技术,2000,23(4):12-15
[64]王利、唐汉云,《一种点火压强峰的控制方法》[J].固体火箭技术,2002,25(1):24-25;
[65] A.K.KM.ulkarni,M.Kumar,K.K.Kuo , Review of solid propellant ignition studies [R].AIAA 1980-1 210
[66] M.A.Eagar. Ignition transient model for large aspect ratio solid motors[R]. AIAA 1996-3 273
[67] J.C.T.Wang.Modern SRM ignition transient modeling (part 5): prospective developments in CFD simulation[R]. AIAA 2001-3 447
[68] J.W.Weber, K.C.Tang, etc. Ignition of composite solid propellants: model development, experiments, and validation[R]. AIAA 2003-4 629
[69] J.C.T. Wang, E.M.Landsbaum, etc. Recent progress in SRM ignition transient modeling[R].AIAA 2003-5 115
[70] J.C.Wang. Experimental study of some problems of small solid propellant rockets[R]. AIAA 1977- 0 902
[71] ZHANG Qiufang, WANG Ningfei, TIAN Weiping. Experimental research of tail-ignition in solid rocket motor[C]. Theory and Practice of Energetic Materials, 2005:698 703
[72] Bennett S J. Carton/motor sample correlation, Final technical report.AD 771808
[73]张旭东、王宏伟、邢耀国、曲凯、王肖飞,《某固体火箭发动机点火启动过程的仿真研究》海军航空工程学院学报,2006,21(3);
[74]谢丽宽、邢耀国,《超期贮存发动机固体推进剂能量特性实验研究》[J].海军航空工程学院学报,2005,20(1):153-156
[75]王志健、杜佳佳,《动网格在固体火箭发动机非稳态工作过程中的应用》,固体火箭技术2008 31(4)西北工业大学航天学院
[76]何洪庆、张振鹏,《固体火箭发动机气体动力学》[M],西安:西北工业大学出版社,1988
[77] T Nagaoka,An Experimental Study on Erosive Burning in Solid Propellant Motor[A]. Proceeding of the Tenth International Symposium on Space Technology and Science [C]. 1973, 83-90.
[78]刑耀国,《火箭发动机控制工程》[M].烟台:海军航空工程学院,1997:191-196
[79]张秋芳、王宁飞、田维平,单项点火试验在小型固体发动机点火设计中的应用,2006年第3期《火工品》
[80]徐向东等,《固体火箭发动机测试与试验技术[M]》,宇航出版社,1994
[81]谢蔚民、吴心平,《固体火箭发动机内弹道异常现象的鉴别》,推进技术,1985(2);
[82]叶定友,《固体火箭发动机故障统计分析》固体火箭推进,1986(2);
[83]张训文、孙维中,《固体火箭发动机内弹道曲线异常的测试诊断方法》,弹箭技术,1986(3)
[84]叶万举等,固体火箭发动机工作过程理论基础[M].国防科技大学,1985.
[2]张平,《从SDI计划重点的转移看固体火箭推进技术的应用前景》,固体火箭推进技术学术会议论文集,1993
[3]王铮、胡永强等,《固体火箭发动机》,中国宇航出版社,1993
[4] Clyde E. Carr Jr., Barbara A. Leary. Solid rockets [J]. Aerospace America, 2010(12)
[5]张旭东,王宏伟,邢耀国等,《某固体火箭发动机点火启动过程的仿真研究》,海军航空工程学院学报,2006,21 (3)
[6]王有元等,《固体火箭发动机设计》,国防工业出版社,1984
[7]李宜敏、张中钦、张远君等,《固体火箭发动机原理》,1999
[8]董师颜、张兆良,《固体火箭发动机原理》,北京理工大学出版社,1996
[9]陈汝训等,《固体火箭发动机设计与研究》,中国宇航出版社,1991
[10]谢蔚民,吴心平.固体火箭发动机内弹道曲线异常现象的鉴别.推进技术, 1985, (2): 7-13
[11]张旭东,王宏伟,邢耀国等.某固体火箭发动机点火启动过程的仿真研究.海军航空工程学院学报, 2006, 21 (3): 319-321.
[12]余贞勇,甘晓松.小型固体发动机尾部药型对点火升压过程的影响.固体火箭技术, 2002, 25 (3): 21-25.
[13]郭凤美,陈步学,吴心平.固体火箭发动机内弹道异常现象的计算机辅助分析.固体火箭技术, 1989, (4): 13-20.
[14]田江桥,张斌兴,张伟青等.固体火箭发动机试验故障分析.上海航天, 2002, (4): 58-61.
[15]金伟娅,《可靠性工程》,北京:化学工业出版社,2005
[16]李进贤,《火箭发动机可靠性》,西北工业大学出版社
[17]北京理工大学一系固体火箭发动机原理[M]北京:北京理工大学出版社,1981
[18]方丁酉、张为华、杨涛等,《固体火箭发动机内弹道学[M]》,长沙:国防科技大学出版社,1997
[19]王磊等,《基于Pro/E软件进行固体火箭发动机内弹道计算的方法初探》,中国新技术新产品,2009年第10期
[20] Coats D E,Levine J N.A Computer Program Prediction of Solid Propellant Rocket Motor Performance Volume I [R],1975
[21]田维平等,《固体发动机药柱CAD及燃烧模型分析》,固体火箭技术,1993年第3期
[22] [俄]A?C?科罗捷耶夫等,《固体火箭发动机气体动力学与热物理过程》,2004
[23]侯林法,《复合固体推进剂》,中国宇航出版社,2005
[24]张书俊,《固体火箭发动机粘弹性药柱结构可靠性分析》,固体火箭技术,2006,29(3):183-187
[25]张书俊、任钧国、吴志桥,《固体火箭发动机药柱点火过程结构可靠性的响应面法》,固体火箭技术,2006,29(6):404-408
[26]潘奠华.固化降温过程中固体火箭发动机材料参数的影响分析[J].烟台大学学报(自然科学与工程版),2006(1):64-67
[27]韦世峰,温度和内压作用下装药结构完整性分析[D].西安:西北工业大学,2006:34.36
[28]蒙上阳.基于粘弹性有限元方法的固体火箭发动机结构完整性分析[D].长沙:国防科技大学,2005
[29]蔡峨,《粘弹性力学基础》,北京航空航天大学出版社
[30]郝松林,《粘弹性力学基础》,科学出版社,1983
[31] Graham.G.and Lee,The Correspondence Principle of Linear Viscoelasticity Theory for Mixed Boundary Value Problems Involving Time-dependent Boundary Regions,Quart.Appl.Math,26,1968
[32] Landel,R.F.and Smith,T.L.,Viscoelasticity Properties of Rubber Like Composite Propellants and Filled Elastomers,J.Am.Rocket Soc.,VOL.31,1961
[33] Parr,C.H.,Deformations and Stresses in Ces-bouded Solid Propellant Grains of Finite Length by Numerical Methods,AD 282055,1962
[34]颜庆津,《数值分析》,北京航空航天大学出版社,1999
[35]谭浩强,《C程序设计》,清华大学出版社,1999
[36]施吉林、刘淑珍、陈桂芝,《计算机数值方法》,高等教育出版社,2002
[37]王心明,《工程压力容器设计与计算》,国防工业出版社,1986
[38]范顺成等,《机械设计基础》,机械工业出版社,2007
[39]王先逵,《机械制造工艺学》,机械工业出版社,1995
[40]蒋友谅,《有限元法基础》,国防工业出版社,1980
[41] O.C.Zienkwich,《有限元法》,科学出版社
[42]谢贻权、何福保,弹性和塑性力学中的有限单元法,机械工业出版社,1982
[43]上海交通大学有限单元法翻译组译,结构和连续力学中的有限单元法,国防工业出版社,1973
[44]龚曙光,《ANSYS工程应用实例解析》,机械工业出版社,2003
[45] MSC.Software.PCL and customization[M].Los Angeles : The Macneal-Schwendler Corporation,2005
[46]隋允康、杜家政、彭细荣等,MSC.Nastran有限元动力分析与优化设计实用教程[M].北京:科学出版社,2004
[47] MSC.software.MSC.Patran user’s manual [M].Los Angeles:The Macneal-Schwendler Corporation,2005
[48]蒙上阳、唐国金、雷勇军等,Burgers模型的参数获取方法[J].固体火箭技术,2003,26(2)
[49] Biot,M.A.,Theory of Stress-Strain Relation in Anisotropic Viscpelasticity and Relaxation Phenomen,J.Appl.Phy.,Vol.25,1954
[50] Coleman,B.D.and Noll,W.,Foundation of Linear Viscoelasticity,Reviews of Modern Physics,Vol.33,1961
[51] Klaus-Jorgen Bathle,《Finite Element Procedures In Engineering Analysis》,Prentice-Hall Inc,1982
[52] Kyuichiro Washizu,《Variation Methods In Eleasticity And Plasticity》,Third Edition,Pergaman Press,1982
[53] Louis Komzsik,《MSC.Nastran 2001 Numerical Method User’s Guide》,MSC.Software
[54]张永昌,《MSC.Nastran有限元分析理论基础与应用》,科学出版社,2004
[55]成一、陈守文,《火工品点火药点火性能的研究》,1003-1480(2001)04-002102
[56] J.A康克林,《烟火化学—基本原理和理论[M]》,陕西秦兴烟火联合公司出版,1988
[57]晋东,《黑火药[M]》,国防工业出版社,1978
[58]王泽山等,《火药实验方法[M]》,兵器工业出版社,1996
[59]屠小昌、王建生,《固体火箭发动机点火药量的计算》,中国航天机电集团公司210所
[60]王光林、蔡峨等,《固体火箭发动机设计》,航空专业教材编审室
[61]石润章、李成忠,《固体火箭发动机点火过程分析》[J]海军航空工程学院学报,2001,16(4):475-477;
[62]屠小昌、王建生,《固体火箭发动机点火药量的计算》[J].固体火箭技术,2000,23(4):5-7;
[63]刘君、张为华、刘伟,《某型号固体火箭发动机点火过程的数值模拟》[J].固体火箭技术,2000,23(4):12-15
[64]王利、唐汉云,《一种点火压强峰的控制方法》[J].固体火箭技术,2002,25(1):24-25;
[65] A.K.KM.ulkarni,M.Kumar,K.K.Kuo , Review of solid propellant ignition studies [R].AIAA 1980-1 210
[66] M.A.Eagar. Ignition transient model for large aspect ratio solid motors[R]. AIAA 1996-3 273
[67] J.C.T.Wang.Modern SRM ignition transient modeling (part 5): prospective developments in CFD simulation[R]. AIAA 2001-3 447
[68] J.W.Weber, K.C.Tang, etc. Ignition of composite solid propellants: model development, experiments, and validation[R]. AIAA 2003-4 629
[69] J.C.T. Wang, E.M.Landsbaum, etc. Recent progress in SRM ignition transient modeling[R].AIAA 2003-5 115
[70] J.C.Wang. Experimental study of some problems of small solid propellant rockets[R]. AIAA 1977- 0 902
[71] ZHANG Qiufang, WANG Ningfei, TIAN Weiping. Experimental research of tail-ignition in solid rocket motor[C]. Theory and Practice of Energetic Materials, 2005:698 703
[72] Bennett S J. Carton/motor sample correlation, Final technical report.AD 771808
[73]张旭东、王宏伟、邢耀国、曲凯、王肖飞,《某固体火箭发动机点火启动过程的仿真研究》海军航空工程学院学报,2006,21(3);
[74]谢丽宽、邢耀国,《超期贮存发动机固体推进剂能量特性实验研究》[J].海军航空工程学院学报,2005,20(1):153-156
[75]王志健、杜佳佳,《动网格在固体火箭发动机非稳态工作过程中的应用》,固体火箭技术2008 31(4)西北工业大学航天学院
[76]何洪庆、张振鹏,《固体火箭发动机气体动力学》[M],西安:西北工业大学出版社,1988
[77] T Nagaoka,An Experimental Study on Erosive Burning in Solid Propellant Motor[A]. Proceeding of the Tenth International Symposium on Space Technology and Science [C]. 1973, 83-90.
[78]刑耀国,《火箭发动机控制工程》[M].烟台:海军航空工程学院,1997:191-196
[79]张秋芳、王宁飞、田维平,单项点火试验在小型固体发动机点火设计中的应用,2006年第3期《火工品》
[80]徐向东等,《固体火箭发动机测试与试验技术[M]》,宇航出版社,1994
[81]谢蔚民、吴心平,《固体火箭发动机内弹道异常现象的鉴别》,推进技术,1985(2);
[82]叶定友,《固体火箭发动机故障统计分析》固体火箭推进,1986(2);
[83]张训文、孙维中,《固体火箭发动机内弹道曲线异常的测试诊断方法》,弹箭技术,1986(3)
[84]叶万举等,固体火箭发动机工作过程理论基础[M].国防科技大学,1985.