自由装填式固体火箭发动机药柱低温点火结构完整性分析
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摘要
利用三维有限元方法,通过热-机耦合,分析一种自由装填式固体火箭发动机药柱从药柱固化降温到低温点火整个过程中发动机的温度场、总位移、等效应力和等效应变的变化情况,得到了固化降温和点火升压过程中药柱/壳体有无粘接两种情况下发动机的受力情况的不同,并根据最大应变能理论,分析了两种情况发动机药柱的结构完整性;得出了在温度和压强双重载荷下,模量、泊松比、药柱/壳体粘接高度等参数对发动机药柱结构完整性的影响规律,表明该型发动机药柱/壳体粘接高度不宜超过40 mm。
By using thermal-structure interaction method of three-dimension viscoelastic finite element software,change of temperature,displacement,Von Mises stress and Von Mises strain of a propellant grain was obtained from the curing temperature of the grain to its ignition pressurization at low temperature.A great difference of the stress-strain state of the grain with and without adhesion between grain/case was found.The integrity of the grain with and without adhesion between grain/case was also analyzed according to the theory of maximum strain energy.The influence of the parameters,include modulus,Poisson ratio,adhesion height of grain/case on the structural integrity of the free loading solid rocket propellant grain subjected to temperature and pressurization load was obtained.The results show that the adhesion height of grain/case should be no more than 40 mm.
By using thermal-structure interaction method of three-dimension viscoelastic finite element software,change of temperature,displacement,Von Mises stress and Von Mises strain of a propellant grain was obtained from the curing temperature of the grain to its ignition pressurization at low temperature.A great difference of the stress-strain state of the grain with and without adhesion between grain/case was found.The integrity of the grain with and without adhesion between grain/case was also analyzed according to the theory of maximum strain energy.The influence of the parameters,include modulus,Poisson ratio,adhesion height of grain/case on the structural integrity of the free loading solid rocket propellant grain subjected to temperature and pressurization load was obtained.The results show that the adhesion height of grain/case should be no more than 40 mm.
引文
[1]LI Fengxiang,LIU Zhongbing,LI Yuesen.Calculation and analysis on structural integrity of solid propellant grains under high acceleration load[C]//IAC-03-S.2.04,54th International Astronautical Congress.The world Space Congress-2003 Sept.29-Oct.3,Bremen,Germany.
[2]Marimuthu R,Rao B Nageswara.Development of efficient finite elements for structural integrity analysis of solid rocket motor propellant grains[J].International Journal of Pressure Vessels and piping,2013,111-112:131-145.
[3]Tejas Nikam,Mrunal Pardeshi,Amit Patil,et al.Structural integrity analysis of propellant in solid rocket motor[C]//International Conference on Ideas,Impact and Innovation in Mechanical Engineering(ICIIIME 2017).2017,5(6):896-902.
[4]ZHOU Dongmo,LIU Xiangyang,SUI Xin,et al.Accelerated aging and structural integrity analysis approach to predict the service life of solid rocket motors[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.July 27-29,2015,FL,2015:1-8
[5]潘奠华,胡明勇,李兵尚.固体推进剂药柱热-机耦合分析及应用[J].烟台大学学报(自然科学与工程版),2005,18(3):216-221.PAN Dianhua,HU Mingyong,LI Bingshang.Thermal-mechanical coupling analysis and application in solid propellants grains[J].Journal of Yantai University(Natural Science and Engineering Edition),2005,18(3):216-221.
[6]丁永强,兰飞强.温度载荷下材料参数对药柱结构完整性的影响[J].航空兵器,2007(5):49-51.DING Yongqiang,LAN Feiqiang.Material parameters influence on grain structure integrity under temperature load[J].Aero Weaponry,2007(5):49-51.
[7]许进升,郑健,鞠玉涛.温度冲击速率对变截面药柱结构完整性的影响[J].江苏航空,2010(增刊):127-130.XU Jinsheng,ZHENG Jian,JU Yutao.Effect of temperature impact rate on structural integrity of variable cross-section grain columns[J].Jiangsu Aviation,2010(supplement):127-130.
[8]高凤莲.某型固体火箭发动机药柱结构完整性研究[D].长沙:国防科技大学,2012,11.GAO Fenglian.Research of structural integrity of a certain solid rocket motor grain[D].Changsha:National University of Defense Technology,2012,11.
[9]郑晓亚,张晓宏,李宏岩,等.自由装填式组合药柱结构完整性分析[J].计算机仿真,2012,29(12):13-16.ZHENG Xiaoya,ZHANG Xiaohong,LI Hongyan,et al.Structure integrity analysis of free loading solid rocket grain under internal pressure[J].Computer Simulation,2012,29(12):13-16.
[10]孟红磊,鞠玉涛,郑健.自由装填式包覆药柱点火过程中应力应变分析[J].江苏航空,2010(增刊):131-134.MENG Honglei,JU Yutao,ZHENG Jian.Stress and strain analysis of free loading clad grain during ignition[J].angsu Aviation,2010(supplement):131-134.
[11]王元有.固体火箭发动机设计[M].北京:国防工业出版社,1984.WANG Yuanyou.Design of solid rocket motor[M].Beijing:National Defense Industry Press,1984.
[2]Marimuthu R,Rao B Nageswara.Development of efficient finite elements for structural integrity analysis of solid rocket motor propellant grains[J].International Journal of Pressure Vessels and piping,2013,111-112:131-145.
[3]Tejas Nikam,Mrunal Pardeshi,Amit Patil,et al.Structural integrity analysis of propellant in solid rocket motor[C]//International Conference on Ideas,Impact and Innovation in Mechanical Engineering(ICIIIME 2017).2017,5(6):896-902.
[4]ZHOU Dongmo,LIU Xiangyang,SUI Xin,et al.Accelerated aging and structural integrity analysis approach to predict the service life of solid rocket motors[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.July 27-29,2015,FL,2015:1-8
[5]潘奠华,胡明勇,李兵尚.固体推进剂药柱热-机耦合分析及应用[J].烟台大学学报(自然科学与工程版),2005,18(3):216-221.PAN Dianhua,HU Mingyong,LI Bingshang.Thermal-mechanical coupling analysis and application in solid propellants grains[J].Journal of Yantai University(Natural Science and Engineering Edition),2005,18(3):216-221.
[6]丁永强,兰飞强.温度载荷下材料参数对药柱结构完整性的影响[J].航空兵器,2007(5):49-51.DING Yongqiang,LAN Feiqiang.Material parameters influence on grain structure integrity under temperature load[J].Aero Weaponry,2007(5):49-51.
[7]许进升,郑健,鞠玉涛.温度冲击速率对变截面药柱结构完整性的影响[J].江苏航空,2010(增刊):127-130.XU Jinsheng,ZHENG Jian,JU Yutao.Effect of temperature impact rate on structural integrity of variable cross-section grain columns[J].Jiangsu Aviation,2010(supplement):127-130.
[8]高凤莲.某型固体火箭发动机药柱结构完整性研究[D].长沙:国防科技大学,2012,11.GAO Fenglian.Research of structural integrity of a certain solid rocket motor grain[D].Changsha:National University of Defense Technology,2012,11.
[9]郑晓亚,张晓宏,李宏岩,等.自由装填式组合药柱结构完整性分析[J].计算机仿真,2012,29(12):13-16.ZHENG Xiaoya,ZHANG Xiaohong,LI Hongyan,et al.Structure integrity analysis of free loading solid rocket grain under internal pressure[J].Computer Simulation,2012,29(12):13-16.
[10]孟红磊,鞠玉涛,郑健.自由装填式包覆药柱点火过程中应力应变分析[J].江苏航空,2010(增刊):131-134.MENG Honglei,JU Yutao,ZHENG Jian.Stress and strain analysis of free loading clad grain during ignition[J].angsu Aviation,2010(supplement):131-134.
[11]王元有.固体火箭发动机设计[M].北京:国防工业出版社,1984.WANG Yuanyou.Design of solid rocket motor[M].Beijing:National Defense Industry Press,1984.