固体火箭发动机燃气科氏加速度的影响分析
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摘要
采用理论分析和试验验证相结合的方法,揭示了过载条件下固体火箭发动机横向过载产生的原因,分析了燃气科氏加速度的影响因素。结果表明,发动机的横向过载是燃气科氏加速度和导弹法向牵连加速度综合作用的结果;燃气科氏加速度与导弹转弯半径呈反比例关系,与导弹速度和燃气速度呈正比例线性关系。地面模拟旋转过载试验结果表明,横向过载将引起Al_2O_3粒子向发动机局部聚集,造成该部位烧蚀加剧,引起喷管收敛段局部烧蚀增大;由于科氏加速度的存在,导致发动机的实际横向过载方向偏离发动机牵连加速度引起的横向过载方向,造成喷管局部烧蚀增大的方向与离心过载方向呈一定的环向偏转角度。
In order to reveal the cause of lateral overload for solid rocket motor(SRM) and analyze influence factors of Coriolis acceleration for combustion exhaust, a method of theoretical analysis and experimental verification is used. The results show that SRM lateral acceleration is a comprehensive effect of Coriolis acceleration and normal implicated one, Coriolis acceleration has an inverse relationship with turning radius of missile and direct linear relationship with missile velocity and combustion exhaust velocity. Simulation rotating overload tests on the ground show that lateral acceleration cause alumina particle aggregation toward SRM surface, which will result in much more serious ablation in this region than others. In addition, Coriolis acceleration will lead to a phenomenon that the direction of real lateral overload is not the direction created by implicated acceleration. Consequently, the direction with much more serious nozzle ablation has a circular angle with implicated acceleration.
In order to reveal the cause of lateral overload for solid rocket motor(SRM) and analyze influence factors of Coriolis acceleration for combustion exhaust, a method of theoretical analysis and experimental verification is used. The results show that SRM lateral acceleration is a comprehensive effect of Coriolis acceleration and normal implicated one, Coriolis acceleration has an inverse relationship with turning radius of missile and direct linear relationship with missile velocity and combustion exhaust velocity. Simulation rotating overload tests on the ground show that lateral acceleration cause alumina particle aggregation toward SRM surface, which will result in much more serious ablation in this region than others. In addition, Coriolis acceleration will lead to a phenomenon that the direction of real lateral overload is not the direction created by implicated acceleration. Consequently, the direction with much more serious nozzle ablation has a circular angle with implicated acceleration.
引文
[1]曹军,郭颜红,邢强.高过载条件下固体火箭发动机工作稳定性研究[J].航空兵器,2014,(1):33-36.
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[4]刘洋,李江,杨飒.过载条件下EPDM绝热材料烧蚀机理和模型研究(Ⅰ)--烧蚀机理分析[J].固体火箭技术,2011,34(2):229-233.
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[10]何国强,王国辉,蔡体敏,等.过载条件下固体火箭发动机内流场数值模拟[J].推进技术,2002,23(3):182-185.(HE Guo-qiang,WANG Guo-hui,CAI Timin,et al.Numerical Simulation on 3-D Two-Phase Flow Field in SRM with Acceleration Load[J].Journal of Propulsion Technology,2002,23(3):182-185.)
[11]李越森,叶定友,利风祥.横向加速度对飞行发动机绝热层烧蚀影响的实验研究[J].航空动力学报,2004,19(2):278-282.
[12]田维平,许团委,王健儒.过载下燃烧室粒子特性与绝热层烧蚀研究进展[J].固体火箭技术,2015,38(1):30-36.
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[14]Kovalev O B.Motor and Plume Particle Size Prediction in Solid-Propellant Rocket Motors[J].Journal of Propulsion and Power,2002,18(6):1199-1210.
[15]何国强,王国辉,蔡体敏,等.高过载条件下固体火箭发动机内流场及绝热层冲蚀研究[J].固体火箭技术,2001,24(4):4-8.
[16]刘洋,吴育飞,李江,等.长时间小过载下发动机流场特征及绝热层烧蚀分析[J].推进技术,2013,34(8):1071-1076.(LIU Yang,WU Yu-fei,LI Jiang,et al.Flow Field and Ablation Mode Analysis of Insulator under Low Acceleration with Long Operation Time Condition for Solid Rocket Motor[J].Journal of Propulsion Technology,2013,34(8):1071-1076.)
[17]李强,杨飒,李江,等.EPDM绝热材料耦合烧蚀模型[J].固体火箭技术,2012,35(1):114-122.
[18]哈尔滨工业大学理论力学教研组.理论力学[M].北京:高等教育出版社,1981.
[19]王开发.哥氏加速度牵连运动为转动时点的加速度合成定理的一种解析证明[J].鞍山钢铁学院学报,1990,13(3):55-58.
[20]胡俊华,齐晓林,冯金富,等.科氏加速度对航炮射击精度的影响[J].火炮发射与控制学报,2003,(4):10-14.
[21]王超,王跃钢,李宁.哥氏加速度对火箭撬试验的影响分析[J].中国惯性技术学报,2010,18(3):378-381.
[22]刘世东.过载对固体火箭发动机影响的研究[J].航空兵器,2006,(6):42-44.
[2]刘洋.高过载固体火箭发动机内流场模拟试验技术[D].西安:西北工业大学,2004.
[3]李江,何国强,陈剑.高过载条件下绝热层烧蚀实验方法研究(Ⅱ)收缩管聚集法[J].推进技术,2004,25(3):196-198.(LI Jiang,HE Guo-qiang,CHEN Jian.Study of Experimental Method for Ablation of Insulator of SRM with High Acceleration(Ⅱ)Convergent Tube Experimental Method[J].Journal of Propulsion Technology,2004,25(3):196-198.)
[4]刘洋,李江,杨飒.过载条件下EPDM绝热材料烧蚀机理和模型研究(Ⅰ)--烧蚀机理分析[J].固体火箭技术,2011,34(2):229-233.
[5]高峰,王建辉,马岑睿.高过载下固体火箭发动机长尾喷管两相流场数值模拟[J].空军工程大学学报(自然科学版),2012,13(1):1-5.
[6]谢文超,徐东来,蔡选义,等.空空导弹推进系统设计[M].北京:国防工业出版社,2007.
[7]郭颜红,梁晓庚,陈斌.大过载下固体火箭发动机工作过程仿真的数学模型[J].航空兵器,2008,(1):21-25.
[8]WU Yuan,HE Guo-qiang,SUN Zhan-peng,et al.Experiment Study of Effects Induced by Overload on SRMPerformance[J].Journal of Solid Rocket Technology,2010,33(5):511-514.
[9]刘洋,李江,何国强,等.过载条件下不同配方体系绝热材料筛选及烧蚀特性[J].推进技术,2011,32(4):569-575.(LIU Yang,LI Jiang,HE Guoqiang,et al.Insulator Material Screen Experiments and Ablation Characteristic under High Acceleration Condition[J].Journal of Propulsion Technology,2011,32(4):569-575.)
[10]何国强,王国辉,蔡体敏,等.过载条件下固体火箭发动机内流场数值模拟[J].推进技术,2002,23(3):182-185.(HE Guo-qiang,WANG Guo-hui,CAI Timin,et al.Numerical Simulation on 3-D Two-Phase Flow Field in SRM with Acceleration Load[J].Journal of Propulsion Technology,2002,23(3):182-185.)
[11]李越森,叶定友,利风祥.横向加速度对飞行发动机绝热层烧蚀影响的实验研究[J].航空动力学报,2004,19(2):278-282.
[12]田维平,许团委,王健儒.过载下燃烧室粒子特性与绝热层烧蚀研究进展[J].固体火箭技术,2015,38(1):30-36.
[13]Sabnis J S,Jong F J,Gibellng H J.Calculation of Particle Trajectories in Solid Rocket Motors with Arbitrary Acceleration[R].AIAA 91-3392.
[14]Kovalev O B.Motor and Plume Particle Size Prediction in Solid-Propellant Rocket Motors[J].Journal of Propulsion and Power,2002,18(6):1199-1210.
[15]何国强,王国辉,蔡体敏,等.高过载条件下固体火箭发动机内流场及绝热层冲蚀研究[J].固体火箭技术,2001,24(4):4-8.
[16]刘洋,吴育飞,李江,等.长时间小过载下发动机流场特征及绝热层烧蚀分析[J].推进技术,2013,34(8):1071-1076.(LIU Yang,WU Yu-fei,LI Jiang,et al.Flow Field and Ablation Mode Analysis of Insulator under Low Acceleration with Long Operation Time Condition for Solid Rocket Motor[J].Journal of Propulsion Technology,2013,34(8):1071-1076.)
[17]李强,杨飒,李江,等.EPDM绝热材料耦合烧蚀模型[J].固体火箭技术,2012,35(1):114-122.
[18]哈尔滨工业大学理论力学教研组.理论力学[M].北京:高等教育出版社,1981.
[19]王开发.哥氏加速度牵连运动为转动时点的加速度合成定理的一种解析证明[J].鞍山钢铁学院学报,1990,13(3):55-58.
[20]胡俊华,齐晓林,冯金富,等.科氏加速度对航炮射击精度的影响[J].火炮发射与控制学报,2003,(4):10-14.
[21]王超,王跃钢,李宁.哥氏加速度对火箭撬试验的影响分析[J].中国惯性技术学报,2010,18(3):378-381.
[22]刘世东.过载对固体火箭发动机影响的研究[J].航空兵器,2006,(6):42-44.