某型喷管扩张段非正常烧蚀的成因分析
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摘要
针对某型喷管试车过程中出现的扩张段非正常烧蚀现象,忽略复杂的烧蚀过程,综合考虑接触热阻、摩擦热耗散过程中的能量分配以及接触对分离后的辐射传热,建立了一种满足工程要求快速分析的固体火箭发动机喷管热结构直接耦合分析方法。分析过程中,重点考察结构间隙这一鲜有讨论的问题,据此定义了2种可能导致该现象的模式,分别分析应力状态及接触对接触行为,最终排除了应力破坏模式,确定间隙烧蚀模式为主要原因。仿真结果与试车结果吻合较好,为喷管后续的改进设计提供了依据。
To research the cause of an abnormal ablation of a nozzle during testing experiment,a fast fully-coupled thermo-structural simulation method was established. This method ignored the complex ablation process and took contact heat resistance,friction heat dissipation and heat radiation between each contact pair into consideration.During analysis,the scarcely mentioned factor,structure gap was focused on. Two possible modes were defined to analysis this phenomenon. By analyzing stress status and contact status of the contact pairs,stress destruction mode was excluded. It was confirmed that the main reason was gap ablation mode. Simulation results from the proposed method indicated that it agreed well with testing experiment. This offered design basis for future improvement.
To research the cause of an abnormal ablation of a nozzle during testing experiment,a fast fully-coupled thermo-structural simulation method was established. This method ignored the complex ablation process and took contact heat resistance,friction heat dissipation and heat radiation between each contact pair into consideration.During analysis,the scarcely mentioned factor,structure gap was focused on. Two possible modes were defined to analysis this phenomenon. By analyzing stress status and contact status of the contact pairs,stress destruction mode was excluded. It was confirmed that the main reason was gap ablation mode. Simulation results from the proposed method indicated that it agreed well with testing experiment. This offered design basis for future improvement.
引文
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[11]张涛,孙冰.固体火箭发动机绝热层温度场的有限元计算方法[J].航空动力学报,2009,24(6):1407-1412Zhang Tao,Sun Bing.Numerical Computation of Solid Rocket Motor Insulation Layer Temperature by Finite Element Method[J].Journal of Aerospace Power,2009,24(6):1407-1412(in Chinese)
[12]Zhang X.Coupled Simulation of Heat Transfer and Temperature of the Composite Rocket Nozzle Wall[J].Aerospace Science&Technology,2011,15(5):402-408
[13]Morozov E V,Pitot de la Beaujardiere J F P.Numerical Simulation of the Dynamic Thermostructural Response of a Composite Rocket Nozzle Throat[J].Composite Structures,2009,91(4):412-420
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[16]王作良.喷管热防护的有限元数值分析[D].哈尔滨:哈尔滨工程大学,2006Wang Zuoliang.A Finite Element Calculation Analysis for Thermal Protection of Nozzle[D].Harbin,Harbin Engineering University,2006(in Chinese)
[17]Goyal V.Structural Analysis of Solid Rocket Motors[C]∥49th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,2008
[18]郑晓亚,陈凤明,蔡飞超.复合喷管热结构耦合计算的一种策略[J].航空动力学报,2011,26(1):223-227Zheng Xiaoya,Chen Fengming,Cai Feichao.Strategy of Thermo-Structure Coupled Computation for Composite Nozzle[J].Journal of Aerospace Power,2011,26(1):223-227(in Chinese)
[19]郑晓亚,王卫祥,蔡飞超,陈凤明.固体火箭发动机喷管热结构一体化计算[J].航空动力学报,2012,27(9):2122-2127Zheng Xiaoya,Wang Weixiang,Cai Feichao,Chen Fengming.Thermo-Structure Integrative Computation for Nozzle in SRM[J].Journal of Aerospace Power,2012,27(9):2122-2127(in Chinese)
[20]田四朋,唐国金,李道奎,袁端才.固体火箭发动机喷管结构间隙设计[J].推进技术,2005,26(5):448-451Tian Sipeng,Tang Guojin,Li Daokui,Yuan Duancai.Gap Design of Solid Rocket Motor Nozzle Structures[J].Journal of Propulsion Technology,2005,26(5):448-451(in Chinese)
[21]郑权.碳/碳复合材料喉衬热结构分析及失效行为研究[D].哈尔滨:哈尔滨工业大学,2011Zheng Quan.Thermo-Structural Analysis And Failure Behavior of C/C Composite Throat[D].Harbin,Harbin Institute of Technology,2011(in Chinese)
[22]Bartz D R.A Simple Equation for Rapid Estimation of Rocket Nozzle Convective Heat Transfer Coefficients[J].Journal of Jet Propulsion,1957,27(1):49-53
[23]李书良,张飞,熊波,侯晓.固体火箭发动机喉衬热结构影响因素分析[J].强度与环境,2013,40(2):56-63Li Shuliang,Zhang Fei,Xiong Bo,Hou Xiao.Influences Factor Analysis of Thermal Structure on Motor Throat[J].Structure&Environment Engineering,2013,40(2):56-63(in Chinese)
[24]朱波,曹伟伟,井敏,董兴广,王成国.C/C复合材料的光谱发射率研究[J].光谱学与光谱分析,2009,29(11):2909-2913Zhu Bo,Cao Weiwei,Jing Min,Dong Xingguang,Wang Chengguo.Study on Spectral Emissivity of C/C Composites[J].Spectroscopy and Spectral Analysis,2009,29(11):2909-2913(in Chinese)
[2]Kumar R R,Vinod G,Renjith S,et al.Thermo-Structural Analysis of Composite Structures[J].Materials Science&Engineering A,2005,412(1):66-70
[3]付鹏,蹇泽群,张钢锤,高波.发动机喷管喉衬烧蚀及热结构工程计算[J].固体火箭技术,2005,28(1):15-19Fu Peng,Jian Zequn,Zhang Gangchui,Gao Bo.Engineering Calculation for Erosion and Thermal Structure of Throat-Insert of a Srm Nozzle[J].Journal of Solid Rocket Technology,2005,28(1):15-19(in Chinese)
[4]史宏斌.固体火箭发动机柔性喷管热分析、静动力响应与实验研究[D].武汉:华中科技大学,1999Shi Hongbin.Thermal and Dynamic Response Analysis and Experimental Study of Flexible Nozzle for Solid Rocket Motor[D].Wuhan,Huazhong University of Science and Technology,1999(in Chinese)
[5]Keswani S T,Andiroglu E,Campbell J D,et al.Recession Behavior of Graphitic Nozzles in Simulated Rocket Motors[J].Journal of Spacecraft&Rockets,2015,22(22):396-397
[6]Kuo K,Keswani K T.A Comprehensive Theoretical Model for Carbon-Carbon Composite Nozzle Recession[J].Combustion Science and Technology,1984,42(3/4):145-164
[7]何洪庆,王思民,牛嵩高,周旭.固体发动机喷管烧蚀和温度场测量[J].固体火箭技术,1993,16(3):31-36He Hongqing,Wang Siming,Niu Songgao,Zhou Xu.The Measurement of Erosion and Temperature Field in a Solid Motor Nozzle[J].Journal of Solid Rocket Technology,1993,16(3):31-36(in Chinese)
[8]Shivakumar K N,Cozart A.Analysis of 3-D Braided Composite Ablative Rocket Nozzle[C]∥ASME 2002 Joint U S-European Fluids Engineering Division Conference.2002:281-288
[9]袁军娅,张振鹏,赵坚,王虎干,刘献伟.固体火箭发动机燃烧室和喷管热防护安全限设计系统[J].固体火箭技术,2002,25(3):17-20Yuan Junya,Zhang Zhenpeng,Zhao Jian,Wang Hugan,Liu Xianwei.Safety Limits Design System of Heat Protection for Combustion Chamber and Nozzle of Solid Rocket Motor[J].Journal of Solid Rocket Technology,2002,25(3):17-20(in Chinese)
[10]Bianchi D,Nasuti F,Martelli E.Coupled Analysis of Flow and Surface Ablation in Carbon-Carbon Rocket Nozzles[J].Journal of Spacecraft&Rockets,2012,46(46):492-500
[11]张涛,孙冰.固体火箭发动机绝热层温度场的有限元计算方法[J].航空动力学报,2009,24(6):1407-1412Zhang Tao,Sun Bing.Numerical Computation of Solid Rocket Motor Insulation Layer Temperature by Finite Element Method[J].Journal of Aerospace Power,2009,24(6):1407-1412(in Chinese)
[12]Zhang X.Coupled Simulation of Heat Transfer and Temperature of the Composite Rocket Nozzle Wall[J].Aerospace Science&Technology,2011,15(5):402-408
[13]Morozov E V,Pitot de la Beaujardiere J F P.Numerical Simulation of the Dynamic Thermostructural Response of a Composite Rocket Nozzle Throat[J].Composite Structures,2009,91(4):412-420
[14]陈汝训.固体火箭发动机设计与研究[M].北京:宇航出版社,1991Chen Ruxun.Solid Rocket Motor Design and Study[M].Beijing,China Astronautic Publishing House,1991(in Chinese)
[15]田四朋,唐国金,李道奎,吴非.固体火箭发动机喷管结构完整性分析[J].固体火箭技术,2005,28(3):180-183Tian Sipeng,Tang Guojin,Li Daokui,Wu Fei.Analysis on Nozzle Structure Integrality of Solid Rocket Motors[J].Journal of Solid Rocket Technology,2005,28(3):180-183(in Chinese)
[16]王作良.喷管热防护的有限元数值分析[D].哈尔滨:哈尔滨工程大学,2006Wang Zuoliang.A Finite Element Calculation Analysis for Thermal Protection of Nozzle[D].Harbin,Harbin Engineering University,2006(in Chinese)
[17]Goyal V.Structural Analysis of Solid Rocket Motors[C]∥49th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,2008
[18]郑晓亚,陈凤明,蔡飞超.复合喷管热结构耦合计算的一种策略[J].航空动力学报,2011,26(1):223-227Zheng Xiaoya,Chen Fengming,Cai Feichao.Strategy of Thermo-Structure Coupled Computation for Composite Nozzle[J].Journal of Aerospace Power,2011,26(1):223-227(in Chinese)
[19]郑晓亚,王卫祥,蔡飞超,陈凤明.固体火箭发动机喷管热结构一体化计算[J].航空动力学报,2012,27(9):2122-2127Zheng Xiaoya,Wang Weixiang,Cai Feichao,Chen Fengming.Thermo-Structure Integrative Computation for Nozzle in SRM[J].Journal of Aerospace Power,2012,27(9):2122-2127(in Chinese)
[20]田四朋,唐国金,李道奎,袁端才.固体火箭发动机喷管结构间隙设计[J].推进技术,2005,26(5):448-451Tian Sipeng,Tang Guojin,Li Daokui,Yuan Duancai.Gap Design of Solid Rocket Motor Nozzle Structures[J].Journal of Propulsion Technology,2005,26(5):448-451(in Chinese)
[21]郑权.碳/碳复合材料喉衬热结构分析及失效行为研究[D].哈尔滨:哈尔滨工业大学,2011Zheng Quan.Thermo-Structural Analysis And Failure Behavior of C/C Composite Throat[D].Harbin,Harbin Institute of Technology,2011(in Chinese)
[22]Bartz D R.A Simple Equation for Rapid Estimation of Rocket Nozzle Convective Heat Transfer Coefficients[J].Journal of Jet Propulsion,1957,27(1):49-53
[23]李书良,张飞,熊波,侯晓.固体火箭发动机喉衬热结构影响因素分析[J].强度与环境,2013,40(2):56-63Li Shuliang,Zhang Fei,Xiong Bo,Hou Xiao.Influences Factor Analysis of Thermal Structure on Motor Throat[J].Structure&Environment Engineering,2013,40(2):56-63(in Chinese)
[24]朱波,曹伟伟,井敏,董兴广,王成国.C/C复合材料的光谱发射率研究[J].光谱学与光谱分析,2009,29(11):2909-2913Zhu Bo,Cao Weiwei,Jing Min,Dong Xingguang,Wang Chengguo.Study on Spectral Emissivity of C/C Composites[J].Spectroscopy and Spectral Analysis,2009,29(11):2909-2913(in Chinese)