固体推进剂药浆流平性对发动机装药结构完整性的影响
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摘要
为分析固体推进剂浇注质量对发动机装药结构完整性的影响,首先采用流平仪对推进剂药浆放置不同时间后的流平性进行了试验,然后通过单轴拉伸试验和微CT扫描试验对相应条件下推进剂的力学性能和孔隙率进行了研究,最后结合有限元计算方法对发动机装药的结构完整性进行了分析。结果表明,随着推进剂药浆放置时间的增加,推进剂流平性逐渐变差,药浆放置5 h后药面有条痕堆积现象,但推进剂的单轴拉伸力学性能差异并不大。通过微CT扫描试验发现,推进剂药浆放置时间由1 h增加到5 h,孔隙率由2.65‰增大至7.97‰,使得推进剂泊松比降低,导致发动机装药在低温点火压力载荷下的变形增大,安全欲度降低。
In order to analyze the effect of solid propellant casting on the structural integrity of SRM grains,the leveling of propellant slurry with different storage period has been tested first by the levelling instrument,and then the uniaxial tension and microCT tests were conducted to study the mechanical properties and porosity of solid propellants,at last the integrity of SRM grain has been analyzed by finite element method.The results show that leveling of propellant slurry is getting worse and the surface of propellant has been streaked when the slurry Store for 5 hours,but the uniaxial tensile mechanical properties of propellants changed little.It was found that the porosity increased from 2.65‰ to 7.97‰ when the placement time of propellant slurry increased from 1 hour to5 hours by microct scanning,so the Poisson's ratio decrease,which immensely deforms the SRM grains and reduce the safety margin under low temperature ignition conditions.
In order to analyze the effect of solid propellant casting on the structural integrity of SRM grains,the leveling of propellant slurry with different storage period has been tested first by the levelling instrument,and then the uniaxial tension and microCT tests were conducted to study the mechanical properties and porosity of solid propellants,at last the integrity of SRM grain has been analyzed by finite element method.The results show that leveling of propellant slurry is getting worse and the surface of propellant has been streaked when the slurry Store for 5 hours,but the uniaxial tensile mechanical properties of propellants changed little.It was found that the porosity increased from 2.65‰ to 7.97‰ when the placement time of propellant slurry increased from 1 hour to5 hours by microct scanning,so the Poisson's ratio decrease,which immensely deforms the SRM grains and reduce the safety margin under low temperature ignition conditions.
引文
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[14]职世君,孙冰,张建伟.考虑泊松比的固体发动机装药贮存寿命预估[J].固体火箭技术,2011,34(5):593-596.ZHI Shijun,SUN Bing,ZHANG Jianwei.Storage life prediction for solid rocket motor grain in consideration of Poisson’s ratio[J].Journal of Solid Rocket Technology,2011,34(5):593-596.
[15]赵伯华,沈月萍.火箭装药体积形变力学特性的研究[J].推进技术,1994,2(2):58-61.ZHAO Bohua,SHEN Yueping.A study on volume deformation mechanical properties of rocket grain[J].Journal of Propulsion Technology,1994,2(2):58-61.
[2]唐汉祥.AP级配和铝粉对HTPB推进剂料浆流变性的影响[J].固体火箭技术,1998,21(1):26-29.TANG Hanxiang.Effect of multimodal AP and Al on rheological behaviour of HTPB propellant slurry[J].Journal of Solid Rocket Technology,1998,21(1):26-29.
[3]王晓飞,李勇宏,胥会祥,等.含微米级AP的HTPB推进剂工艺性能和力学性能[J].火炸药学报,2015,38(1):56-58.WANG Xiaofei,LI Yonghong,XU Huixiang et al.Process properties and mechanical properties of HTPB propellant with micron scale AP[J].Chinese Journal of Explosives&Propellants,2015,38(1):56-58.
[4]唐汉祥.铝粉/HTPB悬浮液的流变性特性[J].固体火箭技术,1996,19(3):23-27.TANG Hanxiang.Rheological behaviour of HTPB suspension filled with aluminum powder[J].Journal of Solid Rocket Technology,1996,19(3):23-27.
[5]Jawalkar S N,Mehilal,Radha K et al.Studies on the effect of plasticiser and addition of toluene diisocyanate at different temperatures in composite propellant formulations[J].Journal of Hazardous Materials,2009,164(2-3):549-554.
[6]Rodic V,Petric M.The effect of additives on solid rocket propellant characteristics[J].Scientific Technical Review,2004,3(4):9-14.
[7]鲁国林.工艺温度对丁羟推进剂力学性能的影响[J].固体火箭技术,1999,22(3):34-36.LU Guolin.Effect of process temperature on mechanical properties of HTPB propellant[J].Journal of Solid Rocket Technology,1999,22(3):34-36.
[8]John Wiley.Rocket propulsion element[M].Hoboken,New Jersey,2010.
[9]赵永翔,赵连起.复合固体推进剂生产中减少气孔的工艺研究[J].火炸药学报,1999(2):37-38.ZHAO Yongxiang,ZHAO Lianqi.Process study on reducing pore in production of solid composite propellant[J].Chinese Journal of Explosives&Propellants,1999(2):37-38.
[10]Ribereau D,Le P Breton,Ballereau S.Casting process effect on composite solid propellant burning rate[R].AIAA 2001-3946.
[11]许进升.复合推进剂粘弹性本构模型实验及数值仿真研究[D].南京:南京理工大学,2013.XU Jinsheng.Experimental and numerical research on thermo-viscoelastic constitutive model of composite propellant[D].Nanjing:Nanjing University of Science&Technology,2013.
[12]张亮,邢国强.某发动机装药结构完整性分析[J].航空兵器,2012(2):29-32.ZHANG Liang,XING Guoqiang.The analysis for grain structural integrity of a certain solid rocket motor[J].Aero Weaponry,2012(2):29-32.
[13]李记威,房雷,李晔鑫,等.含气孔装药固体火箭发动机结构完整性分析[J].航空兵器,2015(4):24-27.LI Jiwei,FANG Lei,LI Yexin et al.Structure integreity analysis of solid rocket motor with cavities[J].Aero Weaponry,2015(4):24-27.
[14]职世君,孙冰,张建伟.考虑泊松比的固体发动机装药贮存寿命预估[J].固体火箭技术,2011,34(5):593-596.ZHI Shijun,SUN Bing,ZHANG Jianwei.Storage life prediction for solid rocket motor grain in consideration of Poisson’s ratio[J].Journal of Solid Rocket Technology,2011,34(5):593-596.
[15]赵伯华,沈月萍.火箭装药体积形变力学特性的研究[J].推进技术,1994,2(2):58-61.ZHAO Bohua,SHEN Yueping.A study on volume deformation mechanical properties of rocket grain[J].Journal of Propulsion Technology,1994,2(2):58-61.