地面与飞行状态下固体发动机比冲差异性分析
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摘要
对固体发动机性能天地差异性产生的原因进行了探究。造成发动机性能天地差异的主要原因在于存在从发动机能量转换到飞行状态下导弹能量的转换效率,其转换效率与导弹的质量比以及导弹飞行速度与发动机等效喷气速度的比值有关;同时,还存在合成视加速度方向与发动机推力方向的偏差以及导弹质量变化等因素对比冲辨识结果的影响。根据现有公开文献报道及相关型号的分析,这些因素造成比冲的差异基本在1 s左右,且在1.5 s以内。分析结果表明,在工程上采用基于视加速度模型和基于遥测压强的发动机内弹道模型均可辨识发动机的比冲,但采用视加速度分析方法进行性能辨识时,需考虑转化效率的修正。
The ground-to-flight performance differences for solid rocket motors are analyzed.The main reason for the difference of motor performances between ground and flight lies in the energy conversion efficiency from motor to missile in flight state,which is related to the mass ratio of missile,and the ratio of the absolute missile flight velocity to the effective motor exhaust velocity with respect to the missile.Besides,the division among the synthetic sensed acceleration direction,the thrust direction of SRM,and the change of missile mass may affect the identification of specific impulse.According to the existing public reports and the analysis of several missiles,the difference of specific impulse for SRM is about 1 s and basically less than 1.5 s.The analysis results show that the specific impulse of the motor can be identified on an engineering basis with the sensed acceleration model and the internal ballistic of motor.However,the correction of conversion efficiency should be considered in performance identification using sensed acceleration analysis method.
The ground-to-flight performance differences for solid rocket motors are analyzed.The main reason for the difference of motor performances between ground and flight lies in the energy conversion efficiency from motor to missile in flight state,which is related to the mass ratio of missile,and the ratio of the absolute missile flight velocity to the effective motor exhaust velocity with respect to the missile.Besides,the division among the synthetic sensed acceleration direction,the thrust direction of SRM,and the change of missile mass may affect the identification of specific impulse.According to the existing public reports and the analysis of several missiles,the difference of specific impulse for SRM is about 1 s and basically less than 1.5 s.The analysis results show that the specific impulse of the motor can be identified on an engineering basis with the sensed acceleration model and the internal ballistic of motor.However,the correction of conversion efficiency should be considered in performance identification using sensed acceleration analysis method.
引文
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[2]Langhenry M T,Parks J M.Reconstruction of flight specific impulse for solid propellant motors[R].AIAA 91-2428.
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[5]赵金萍,余贞勇,弓亚涛.固体火箭发动机性能天地差异性探讨[J].固体火箭技术,2017,40(2):135-140.ZHAO Jinping,YU Zhenyong,GONG Yatao.Discussion on ground-to-flight performance difference of SRM[J].Journal of Solid Rocket Technology,2017,40(2):135-140.
[6]George P Sutton,Oscar Biblarz.Rocket propulsion elements(Eighth Edition)[M].New Jersey:A Wiley-interscience Publicationby.2010.
[7]陆元九.惯性器件[M].北京:中国宇航出版社,2009.
[2]Langhenry M T,Parks J M.Reconstruction of flight specific impulse for solid propellant motors[R].AIAA 91-2428.
[3]刘格军.基于视加速度固体火箭发动机飞行比冲估算[J].固体火箭技术,2008,31(5):464-465.LIU Gejun.Calculation of specific impulse of soid rocket motor based on visual acceleration[J].Journal of Solid Rocket Technology,2008,31(5):464-465.
[4]何景轩,田维平,余贞勇.飞行状态下固体火箭发动机比冲计算[J].固体火箭技术,1999,22(4):7-9.HE Jingxuan,TIAN Weiping,YU Zhenyong.Calculation of specific impulse of solid rocket motor in flight[J].Journal of Solid Rocket Technology,1999,22(4):7-9.
[5]赵金萍,余贞勇,弓亚涛.固体火箭发动机性能天地差异性探讨[J].固体火箭技术,2017,40(2):135-140.ZHAO Jinping,YU Zhenyong,GONG Yatao.Discussion on ground-to-flight performance difference of SRM[J].Journal of Solid Rocket Technology,2017,40(2):135-140.
[6]George P Sutton,Oscar Biblarz.Rocket propulsion elements(Eighth Edition)[M].New Jersey:A Wiley-interscience Publicationby.2010.
[7]陆元九.惯性器件[M].北京:中国宇航出版社,2009.