15:1气氧/煤油变推力火箭发动机设计及试验
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摘要
为了进一步提高变推力火箭发动机推力调节水平、拓宽推进剂使用范围、提升调节控制的技术能力,采用理论计算和地面试验的方法,设计了一款基于机械定位双调系统的气氧/煤油变推力火箭发动机,对变推力发动机的性能、针栓式喷注器的性能和机械定位双调系统的调节效果进行了研究。结果表明:气氧/煤油变推力火箭发动机在0.26～4.35MPa室压实现稳定燃烧,推力变化为57.30～864.70N,推力变化比达到15:1,最高燃烧效率达到97.14%;流量调节阀可精确调节推进剂流量,针栓式喷注器可主动控制喷注压降,达到机械定位双调系统的预期目标,展现出采用机械定位双调系统的该型变推力火箭发动机在深度变推力技术应用的优势。
In order to improve the thrust adjustment level,broaden the use of propellant,enhance the control ability of thrust rocket engine,a GO_2/kerosene variable-thrust rocket engine based on mechanical positioning dual-modulation scheme was designed by using theoretical calculations and ground test methods. The performance of variable-thrust engine and pintle injector,as well as the adjusting effect of mechanical positioning dual-modulation scheme were studied. The results show GO_2/kerosene variable thrust rocket engine achieves stable combustion at 0.26～4.35 MPa and generates 57.30～864.70 N of thrust. Thrust variation ratio is 15. The maximum combustion efficiency is 97.14%. Besides,the flow control valve can accurately adjust the propellant flow and the pintle injector can actively control the injection pressure drop. Mechanical positioning dual-modulation scheme achieves the desired purpose. The variable thrust rocket engine shows the advantages of the mechanical positioning dual-modulation scheme in the application of the deep variable-thrust technology.
In order to improve the thrust adjustment level,broaden the use of propellant,enhance the control ability of thrust rocket engine,a GO_2/kerosene variable-thrust rocket engine based on mechanical positioning dual-modulation scheme was designed by using theoretical calculations and ground test methods. The performance of variable-thrust engine and pintle injector,as well as the adjusting effect of mechanical positioning dual-modulation scheme were studied. The results show GO_2/kerosene variable thrust rocket engine achieves stable combustion at 0.26～4.35 MPa and generates 57.30～864.70 N of thrust. Thrust variation ratio is 15. The maximum combustion efficiency is 97.14%. Besides,the flow control valve can accurately adjust the propellant flow and the pintle injector can actively control the injection pressure drop. Mechanical positioning dual-modulation scheme achieves the desired purpose. The variable thrust rocket engine shows the advantages of the mechanical positioning dual-modulation scheme in the application of the deep variable-thrust technology.
引文
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[8] Muelier T,Dressier G. TRW 40 klbf LOX/RP-1 Low Cost Pintle Engine Test Results[R]. AIAA 2000-3863.
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[11]邢馥源.双组元变推力火箭发动机喷注器改进设计[J].推进技术,1990,11(2):42-45.(XING Fu-yuan. Improved Design of Bipropellants Variable Thrust Rocket Engine Injector[J]. Journal of Propulsion Technology,1990,11(2):42-45.)
[12]易新郁.双调变推力液体火箭发动机的关机[J].推进技术,1992,13(1):44-49.(YI Xin-yu. Shutdown of Dual-Regulation Variable Thrust Liquid Rocket Engine[J]. Journal of Propulsion Technology,1992,13(1):44-49.)
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[14]刘昌波,兰晓辉,陈炜.月球探测器变推力液体火箭发动机技术研究[C].北京:第八届国际月球探测与应用大会,2006.
[15]雷娟萍,兰晓辉,章荣军,等.嫦娥三号探测器7500N变推力发动机研制[J].中国科学:技术科学,2014,(6):569-575.
[16]朱忠惠.导弹与航天丛书-推力矢量控制伺服系统[M].北京:宇航出版社,2006.
[2]姜清伟.变推力液体火箭发动机试验研究[J].推进技术,1988,9(6):12-15.(JIANG Qing-wei. Experimental Research on Variable Thrust Liquid Rocket Engine[J]. Journal of Propulsion Technology,1988,9(6):12-15.
[3] Dressier G A,Bauer J M. TRW Pintle Engine Heritage and Performance Characteristics[R]. AIAA 2000-3871
[4] Elverum G Jr,Staudhammer P. The Descent Engine for the Lunar Module[R]. AIAA 67-521.
[5] Gilroy R,Sackheim R. The Lunar Module Descent Engine-A Historical Summary[R]. AIAA 89-2385.
[6] Ono D K,Dressier G A,Kruse W D,et al. The Design,Development,and Qalification of an Advanced Columbium Liquid Apogee Engine(Ac-Lae)[R]. AIAA98-3671.
[7] Hardgrove J H,Krieg J R. High Performance Throttling and Pulsing Rocket Engine[R]. AIAA 84-1254.
[8] Muelier T,Dressier G. TRW 40 klbf LOX/RP-1 Low Cost Pintle Engine Test Results[R]. AIAA 2000-3863.
[9] Capozzoli M P,Shotwell M G,Fincher M L. The Nalcon 9:A New Eelv-Class Man-Rated Launch Vehicle[C]. Hyderabad:58th International Astronautical Congress,2007.
[10]旷武岳.变推力液体火箭发动机的发展[C].长沙:中国宇航学会液体火箭推进专业第五届学术会议,1990.
[11]邢馥源.双组元变推力火箭发动机喷注器改进设计[J].推进技术,1990,11(2):42-45.(XING Fu-yuan. Improved Design of Bipropellants Variable Thrust Rocket Engine Injector[J]. Journal of Propulsion Technology,1990,11(2):42-45.)
[12]易新郁.双调变推力液体火箭发动机的关机[J].推进技术,1992,13(1):44-49.(YI Xin-yu. Shutdown of Dual-Regulation Variable Thrust Liquid Rocket Engine[J]. Journal of Propulsion Technology,1992,13(1):44-49.)
[13]章荣军,林革,李福云.变推力液体火箭发动机技术研究[C].西安:第五届液体火箭推进技术发展研讨会,2005.
[14]刘昌波,兰晓辉,陈炜.月球探测器变推力液体火箭发动机技术研究[C].北京:第八届国际月球探测与应用大会,2006.
[15]雷娟萍,兰晓辉,章荣军,等.嫦娥三号探测器7500N变推力发动机研制[J].中国科学:技术科学,2014,(6):569-575.
[16]朱忠惠.导弹与航天丛书-推力矢量控制伺服系统[M].北京:宇航出版社,2006.