富氧补燃循环液氧煤油发动机深度推力调节方案对比分析
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摘要
针对富氧补燃循环液氧煤油发动机目前推力调节范围窄的问题,以某型富氧补燃循环液氧煤油发动机为原型,建立了发动机非线性静态数学模型,利用Matlab计算分析了5种推力调节方案,其中调节推力室供应路流量的方案不可行;调节燃气发生器燃料路流量会引起燃气发生器混合比严重偏离稳定工作点;联合调节燃气发生器燃料路和氧路流量使得系统复杂;调节涡轮燃气流量可获得较宽推力调节范围,未来将针对该调节方案开展技术研究。
Thrust of the oxidizer-rich gas staged combustion liquid oxidizer/kerosene engine should be able to vary over a wide range to meet the requirements of deep space exploration in the future, however the thrust can only vary over a small range at present. A nonlinear mathematical model of oxidizer-rich gas staged combustion liquid oxidizer/kerosene engine was established to solve the problem. Five types of thrust throttling schemes were calculated and analyzed with Matlab. The results showed that regulating the fuel flow rate of the combustion chamber was impossible; Adjusting the fuel flow rate of gas generator resulted in a serious deviation of mixture ratio which would cause unsteady operation. A combined regulation of the oxidizer and fuel supply of the gas generator increased the complexity of the system. Changing the gas flow through the turbine was feasible to accomplish deep throttling which will be further investigated in the future.
Thrust of the oxidizer-rich gas staged combustion liquid oxidizer/kerosene engine should be able to vary over a wide range to meet the requirements of deep space exploration in the future, however the thrust can only vary over a small range at present. A nonlinear mathematical model of oxidizer-rich gas staged combustion liquid oxidizer/kerosene engine was established to solve the problem. Five types of thrust throttling schemes were calculated and analyzed with Matlab. The results showed that regulating the fuel flow rate of the combustion chamber was impossible; Adjusting the fuel flow rate of gas generator resulted in a serious deviation of mixture ratio which would cause unsteady operation. A combined regulation of the oxidizer and fuel supply of the gas generator increased the complexity of the system. Changing the gas flow through the turbine was feasible to accomplish deep throttling which will be further investigated in the future.
引文
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[4] 雷娟萍,兰晓辉,章荣军,等.嫦娥三号探测器7500 N变推力发动机研制[J].中国科学:技术科学,2014,44(6):569-575.Lei J P,Lan X H,Zhang R J,et al.Development of 7500 N variable thrust engine of Chang’e-3[J].Science China:Technological Sciences,2014,44(6):569-575.(in Chinese)
[5] 李斌,张小平,马冬英.我国新一代载人火箭液氧煤油发动机[J].载人航天,2014,20(5):427-431.Li B,Zhang X P,Ma D Y.The LOX / Kerosene rocket engine for Chinese new-generation manned launch vehicle[J].Manned Spaceflight,2014,20(5):427-431.(in Chinese)
[6] 果琳丽,王平,梁鲁,等.载人月面着陆及起飞技术初步研究[J].航天返回与遥感,2013,36(4):10-16.Guo L L,Wang P,Liang L,et al.Preliminary research on manned lunar landing and lifting off technology[J].Spacecraft Recovery & Remote Sensing,2013,36(4):10-16.(in Chinese)
[7] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005:27-70.Zhang G T.High Pressure Staged Combustion LOX/Kerosene Rocket Engine[M].Beijing:National Defense Industry Press,2005:27-70.(in Chinese)
[8] 奥夫相尼科夫Б B,博罗夫斯基Б И.液体火箭发动机涡轮泵装置原理与计算[M].任汉芬,夏德新,译.北京:航天工业总公司第十一研究所,1999:322-398.Ovsiannikov B V,Borjvskii B I.Theory and Calculation of Turbo-pump in Liquid Rocket Engine[M].Ren H F,Xia D X,Translate.Beijing:Eleventh Graduate School of Space Industry Company,1999:322-398.(in Chinese)
[9] Sutton G P.History of liquid-propellant rocket engines in Russia,formerly the Soviet Union[J].Journal of Propulsion and Power,2003,19(6):1008-1037。
[10] 陈宏玉,刘红军.补燃循环发动机推力调节过程建模与仿真研究[J].火箭推进,2014,40(1):18-24.Chen H Y,Liu H J.Modeling and simulations on the thrust regulation process of staged combustion cycle rocket engine[J].Journal of Rocket Propulsion,2014,40(1):18-24.(in Chinese)