基于T型燃烧器的非线性不稳定参数分析
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摘要
基于脉冲触发T型燃烧器技术,对T型燃烧器内的平衡压强上升(DC Shift)和初始极限幅值进行测量,获得DC Shift、初始极限振幅以及压强耦合响应函数(Rp)三者之间的相互关系。实验结果表明,T型燃烧器中可测量得到推进剂燃烧产生的平衡压强上升现象,且与初始极限振荡幅值的二次方成正比;推进剂配方对DC Shift影响较大,即压强耦合响应函数值越高,推进剂燃烧产生DC Shift越大;推进剂压强耦合响应函数、初始极限幅值和DC Shift三者之间存在一定的耦合关系,这一结果与Flandro的平衡压强上升理论基本一致。
Based on the pulsing trigger T-burner technique,some results were obtained on the relationship between the DC Shift,the initial limit amplitude and the pressure coupled response function. The result shows that,the propellant combustion has a great influence on the DC Shift and the initial limit amplitude. Also,the propellant with different formulations has a great influence on the DC Shift,which means that the higher the pressure response functions,the bigger DC Shift produced by the propellant burning would be. For nonlinear instability,there is a certain coupling relationship between the pressure response function of the propellant,the initial limit amplitude and the DC Shift,and the results are consistent with the theory of Flandro.
Based on the pulsing trigger T-burner technique,some results were obtained on the relationship between the DC Shift,the initial limit amplitude and the pressure coupled response function. The result shows that,the propellant combustion has a great influence on the DC Shift and the initial limit amplitude. Also,the propellant with different formulations has a great influence on the DC Shift,which means that the higher the pressure response functions,the bigger DC Shift produced by the propellant burning would be. For nonlinear instability,there is a certain coupling relationship between the pressure response function of the propellant,the initial limit amplitude and the DC Shift,and the results are consistent with the theory of Flandro.
引文
[1]Blomshield F S,Mathes H B,Crump J E,et al.Nonlinear stability testing of full-scale tactical motors[J].Journal of Propulsion and Power,1997,13(3):356-366.
[2]Flandro G A,Fischbach S R,Majdalani J,et al.Nonlinear rocket motor stability prediction:limit amplitude,triggering and mean pressure shift[R].AIAA 2004-4054.
[3]Malhotra S,Flandro G A.On nonlinear combustion instability[J].AIAA 97-3250.
[4]刘佩进,金秉宁,李强.战术导弹固体发动机燃烧不稳定研究概述[J].固体火箭技术,2012,35(4):446-449+456.
[5]胡大宁,何国强,刘佩进,等.翼柱型药柱固体火箭发动机不稳定燃烧研究[J].固体火箭技术,2010,33(5):502-506.
[6]Culick F E C.Acoustic oscillations in solid propellant rocket chambers[J].Acta Astronautica,1966,12(2):113-126.
[7]Culick F E C.Unsteady motions in combustion chambers for propulsion systems[M].Virginia:National Technical Information Service Springfield,2006.
[8]Culick F E C.Nonlinear behavior of acoustic waves in combustion chambers[R].Jet Propulsion Laboratory,NASA,April 1975,NASA-CR-149376.
[9]Flandro G A.Energy balance analysis of nonlinear combustion instability[J].Journal of Propulsion and Power,1985,1(3):210-221.
[10]Flandro G A.Approximate analysis of nonlinear instability with shock waves[R].AIAA 82-1220.
[11]Baum J D,Levinet J N,Lovine R L.Pulsed instability in rocket motors:a comparison between predictions and experiments[J].Journal of Propulsion and Power,1988,4(4):308-316.
[12]French J C,Flandro G A,Majdalani J.Improvements to the linear standard stability prediction program(SSP)[R].AIAA 2004-4181.
[13]Flandro G A,Majdalani J,French J C.Incorporation of nonlinear capabilities in the standard stability prediction program[R].AIAA 2004-4182.
[14]刘佩进,齐宗满,金秉宁,等.两种含铝复合推进剂压强耦合响应的试验对比[J].固体火箭技术,2013,36(1):83-88.
[2]Flandro G A,Fischbach S R,Majdalani J,et al.Nonlinear rocket motor stability prediction:limit amplitude,triggering and mean pressure shift[R].AIAA 2004-4054.
[3]Malhotra S,Flandro G A.On nonlinear combustion instability[J].AIAA 97-3250.
[4]刘佩进,金秉宁,李强.战术导弹固体发动机燃烧不稳定研究概述[J].固体火箭技术,2012,35(4):446-449+456.
[5]胡大宁,何国强,刘佩进,等.翼柱型药柱固体火箭发动机不稳定燃烧研究[J].固体火箭技术,2010,33(5):502-506.
[6]Culick F E C.Acoustic oscillations in solid propellant rocket chambers[J].Acta Astronautica,1966,12(2):113-126.
[7]Culick F E C.Unsteady motions in combustion chambers for propulsion systems[M].Virginia:National Technical Information Service Springfield,2006.
[8]Culick F E C.Nonlinear behavior of acoustic waves in combustion chambers[R].Jet Propulsion Laboratory,NASA,April 1975,NASA-CR-149376.
[9]Flandro G A.Energy balance analysis of nonlinear combustion instability[J].Journal of Propulsion and Power,1985,1(3):210-221.
[10]Flandro G A.Approximate analysis of nonlinear instability with shock waves[R].AIAA 82-1220.
[11]Baum J D,Levinet J N,Lovine R L.Pulsed instability in rocket motors:a comparison between predictions and experiments[J].Journal of Propulsion and Power,1988,4(4):308-316.
[12]French J C,Flandro G A,Majdalani J.Improvements to the linear standard stability prediction program(SSP)[R].AIAA 2004-4181.
[13]Flandro G A,Majdalani J,French J C.Incorporation of nonlinear capabilities in the standard stability prediction program[R].AIAA 2004-4182.
[14]刘佩进,齐宗满,金秉宁,等.两种含铝复合推进剂压强耦合响应的试验对比[J].固体火箭技术,2013,36(1):83-88.