General Technical Review of Long March 5 Liquid Oxygen Kerosene Engine

Abstract

High pressure staged combustion liquid oxygen kerosene engine is used in the boosters of Long March 5 (LM-5, CZ-5) launch vehicle. The engine adopts high pressure staged combustion cycle, and has the characteristics of high performance, self-starting, wide range of thrust and mixing ratio adjustment and compact structure. In this paper, the development history and technical scheme characteristics of LM-5 launch vehicle’s liquid oxygen kerosene engine are reviewed. The key technologies in the development of the parallel mode engines are analyzed emphatically, such as self-starting ignition technology, large time difference asynchronous shutdown technology and low frequency characteristics of structure in YF-100 engine single mode and two-engine parallel mode. The improvement of performance enhancement, structure lightening, reliability growth and full mission environmental adaptability for YF-100 engine, as well as the demand for high-precision online fault diagnosis system for liquid oxygen kerosene engine, is proposed.

Keywords

Long March 5 / LOX /kerosene engine / self-starting / low frequency characteristics

References

[1] 李东,王珏,何巍,等. 长征五号运载火箭总体方案及关键技术[J]. 导弹与航天运载技术,2017(3):1-5
LI D,WANG J,HE W,et al. The general scheme and key technologies of CZ-5 launch vehicle[J]. Missiles and Space Vehicles,2017(3):1-5
[2] 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.
[3] 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
[4] 侯瑞峰，陈建华，曹晨. 高室压液氧烃发动机冷却结构适应性分析[C]//中国航天第三专业信息网第四十届技术交流会暨第四届空天动力联合会议论文集——S02液体推进及相关技术. 昆明：中国航天第三专业信息网，2019.
[5] 曹晨,陈建华,赵剑,等. 大直径液氧煤油发动机燃烧室抗脉动隔板技术[J]. 推进技术,2019,40(2):331-338
CAO C,CHEN J H,ZHANG J,et al. Investigation on anti-pulsating baffle of large diameter LOX/kerosene rocket engine combustor[J]. Journal of Propulsion Technology,2019,40(2):331-338
[6] 李龙飞,陈建华,刘站国. 大推力液氧煤油补燃发动机高频燃烧不稳定性的控制方法[J]. 导弹与航天运载技术,2011(3):16-19
LI L F,CHEN J H,LIU Z G. Control techniques of high frequency combustion instability for high thrust LOX/kerosene staged combustion cycle engine[J]. Missiles and Space Vehicles,2011(3):16-19
[7] 陈晖,李斌,张恩昭,等. 液体火箭发动机高转速诱导轮旋转空化[J]. 推进技术,2009,30(4):390-395
CHEN H,LI B,ZHANG E Z,et al. Rotating cavitation of the high-speed rotational inducer of LPRE[J]. Journal of Propulsion Technology,2009,30(4):390-395
[8] 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
[9] 徐浩海,刘站国. 补燃循环发动机起动过程涡轮功率控制[J]. 火箭推进,2006,32(4):10-14
XU H H,LIU Z G. Turbine power control of staged combustion cycle engine during start-up[J]. Journal of Rocket Propulsion,2006,32(4):10-14
[10] 陈宏玉,刘红军,陈建华. 补燃循环发动机强迫起动过程[J]. 航空动力学报,2015,30(12):3010-3016
CHEN H Y,LIU H J,CHEN J H. Forced start-up procedure of a staged combustion cycle engine[J]. Journal of Aerospace Power,2015,30(12):3010-3016
[11] 谢廷峰,刘洪刚,黄强,等. 液体火箭发动机地面试车实时故障检测算法[J]. 航天控制,2008,26(1):74-78
XIE T F,LIU H G,HUANG Q,et al. Real time fault detection algorithm for liquid-propellant rocket engine ground test[J]. Aerospace Control,2008,26(1):74-78
[12] 周磊,朱子环,耿卫国,等. 美国液体火箭发动机试验中健康管理技术研究进展[J]. 导弹与航天运载技术,2013(5):20-25
ZHOU L,ZHU Z H,GEN W G,et al. Latest development of health management technology on liquid rocket engine test in the USA[J]. Missiles and Space Vehicles,2013(5):20-25
[13] FIORUCCI T R，LAKIN D R，REYNOLDS T D. Advanced engine health management applications of the SSME real-time vibration monitoring system：AIAA 2000-3622[R]. [S. l. ]：AIAA，2000.
[14] JOST K. NASA's space launch initiative[J]. Aerospace engineering (Society of Automotive Engineers),2003,23(5):24-28
[15] GUO T H，MERRILL W，DUYAR A. Real-time diagnostics for a reusable rocket engine：NASA-TM-105792[R]. USA：NASA，1992.
[16] PETTIT C D，BARKHOUDARIAN S. Reusable rocket engine advanced health management system. architecture and technology evaluation-summary[C]//35th Joint Propulsion Conference and Exhibit. California：AIAA，1999.
[17] 于海昌,贾成文. 大型捆绑火箭振动试验液体取代与支撑影响修正方法[J]. 强度与环境,1996(1):25-33
YU H C,JIA C W. Liquid substitution and suspension influence correction methods for large scale launch rocket[J]. Structure and Environment Engineering,1996(1):25-33
[18] 于海昌. 大型火箭振动试验振型斜率测试方法[J]. 强度与环境,1996(3):45-53
YU H C. Mode shape slopes measurement methods for large scale rocket vibration test[J]. Structure and Environment Engineering,1996(3):45-53
[19] 王建民,荣克林,冯颖川,等. 捆绑火箭全箭动力学特性研究[J]. 宇航学报,2009,30(3):821-826
WANG J M,RONG K L,FENG Y C,et al. The research of dynamic characteristics for the strap-on launch vehicle[J]. Journal of Astronautics,2009,30(3):821-826
[20] 黄其殷. 补燃循环发动机双机并联结构低频特性研究[D]. 西安：西安航天动力研究所，2010.
HUANG Q Y. Study on low-frequency structure characteristics of double parallel of staged combustion cycle engine[D]. Xi’an：Xi’an Aerospace Propulsion Institute，2010.