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弹箭与制导学报 >

2025 , Vol. 45 >Issue 5: 735 - 741

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.05.017

学术文章

高空机降低起动超调方法

  • 姜勇 ,
  • 王冠男 ,
  • 张涛 ,
  • 罗文
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  • 西安航天动力研究所, 陕西 西安 710100

姜勇(1986—),男,高级工程师。邮箱:

收稿日期: 2025-01-07

  网络出版日期: 2025-11-28

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Method of Reduction Overshoot of High Altitude Rocket Engine Startup Process

  • JIANG Yong ,
  • WANG Guan Nan ,
  • ZHANG Tao ,
  • LUO Wen
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  • Xi’an Aerospace Propulsion Institute, Xi’an, 710100, Shaanxi, China

Received date: 2025-01-07

  Online published: 2025-11-28

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摘要

以开式循环火箭发动机起动系统为研究对象,针对高空起动过程中超调较大的现象进行研究,认为起动超调主要原因在于起动过程中装药燃烧与燃气发生器叠加工作时间长。利用系统仿真模型,研究了副阀与主阀打开时间对起动超调的影响,并提出了一种通过延迟副阀打开时间,减少装药与燃气发生器共同工作时间的方式实现降低超调的方法。首先,验证了计算模型与试验数据的吻合性,计算了副阀打开时间与主阀打开时间对起动超调的影响;其次,通过地面热试车,确定了降低起动超调方法的效果,并研究了该方法对发动机起动加速性的影响;最后确定了改进方案并应用于火箭飞行中,将发动机超调量降低至10%以下,验证了方法的有效性与可靠性。

关键词： 起动超调; 起动过程; 起动程序; 火箭发动机; 地面试车

本文引用格式

姜勇 , 王冠男 , 张涛 , 罗文 . 高空机降低起动超调方法[J]. 弹箭与制导学报, 2025 , 45(5) : 735 -741 . DOI: 10.15892/j.cnki.djzdxb.2025.05.017

Abstract

Taking the start-up system of open cycle rocket engine as the research object,this paper studies the problem of overshoot in the start-up process of the high altitude rocket engine.The reason of overshoot is the combined working of powder charge and gas generator for a long time during start-up process.The mathematical model of describing the start-up process of engine is established.This paper also studies the effect of the opening time of the auxiliary valve and the main valve on the starting process by using the simulation model.A method to reduce overshoot by delaying the opening time of the auxiliary valve is proposed.Firstly,the agreement between the simulation model and the experimental data is verified.The influence of the opening time of the auxiliary valve and the opening time of the fuel valve on the overshoot of starting is calculated.Secondly,the method of reducing the overshoot is proved to be valid by the ground test,and it has an effect on the acceleration of engine starting.Finally,the method is applied in rocket flight,and then the overshoot of the engine is reduced to less than 10%.It shows that method of reduction overshoot is effective and reliable.

Key words： overshoot; startup process; startup time sequence; ground test; ground test

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序
[1]
刘上, 王艺杰, 程晓辉, 等. 小推力泵压式发动机自身起动过程仿真分析[J]. 火箭推进, 2016, 42(4):7-13.

LIU S, WANG Y J, CHENG X H, et al. Simulation of self start-up process for low thrust pump-fed rocket engine[J]. Journal of Rocket Propulsion, 2016, 42(4):7-13.

[2]
杨明磊, 张黎辉. 液氧/煤油补燃循环发动机起动过程研究[J]. 火箭推进, 2009, 35(1):21-26.

YANG M L, ZHANG L H. Study on start-up of the staged combustion LOX/kerosene rocket engine[J]. Journal of Rocket Propulsion, 2009, 35(1):21-26.

[3]
陈艳霞, 关世玺, 唐家鹏. 火箭发动机起动过程动力学研究[J]. 弹箭与制导学报, 2010, 30(5):131-136.

DOI

CHEN Y X, GUAN S X, TANG J P. The Research of Start Dynamics for Rocket Engine[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2010, 30(5):131-136.

[4]
李元启, 刘红军, 徐浩海, 等. 液体火箭发动机动态特性仿真技术研究进展[J]. 火箭推进, 2017, 43(5):1-6.

LI Y Q, LIU H J, XU HH, et al. Research progress on numerical simulation technology of liquid rocket engine dynamic characteristics[J]. Journal of Rocket Propulsion, 2017, 43(5):1-6.

[5]
JUNG T, LEE S, KWONS. Dynamic characteristics of a bellows-type mixture-ratio stabilizer for a liquid rocket engine[J]. Journal of Spacecraft and Rockets, 2010, 47(5):849-856.

DOI

[6]
管杰, 刘上, 刘志让. 补燃发动机完全自身起动过程富氧燃气温度控制[J]. 火箭推进, 2020, 46(3):33-40.

GUAN J, LIU S, LIU Z R. Temperature control of oxygen-riched gas during complete self start-up process for staged combustion cycle engine[J]. Journal of Rocket Propulsion, 2020, 46(3):33-40.

[7]
管杰, 何宏疆, 董万峰, 等. 流量调节器快速起调过程[J]. 火箭推进, 2022, 48(05):61-68.

GUAN J, HE H J, DONG W F, et al. Rapid start-up process of liquid-flow regulator[J], Journal of Rocket Propulsion, 2022, 48(05):61-68.

[8]
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.

[9]
姜垒, 刘上, 刘志让, 等. 燃气发生器点火接力过程对发动机起动性能的影响[J]. 火箭推进, 2021, 47(03):74-81.

JIANG L, LIU S, LIU Z R, et al. Influence of ignition relay process of gas generator on starting performance of engines[J]. Journal of Rocket Propulsion, 2021, 47(03):74-81.

[10]
KARIMI H, NASSIRHARAND A, BEHESHTI M. Dynamic and nonlinear simulation of liquid propellant engines[J]. Journal of propulsion and power. 2003, 19(5):9338-944.

[11]
BINDER M. A transient model of the RL10A-3-3A rocket engine[C]// 31st Joint propulsion conference and exhibit.San Diego.CA.USA.Reston. Virigina:AIAA, 1995

[12]
LYTLE J K. The numerical propulsion system simulation:a multidisciplinary design system for aerospace vehicles[C]// 14th international symposium on air breathing engines.Italy:[s.n.], 1999.

[13]
Sarra S A. Chebyshev super spectral viscosity method for a two-dimensional fluidized bed medel[J]. Internation Journal for Numerical Methods in Fluids, 2022(4):1-19.

[14]
俞骏, 周韦韦, 刘景源. 一种三通道进气先进旋涡燃烧室性能数值分析[J]. 弹箭与制导学报, 2017, 37(4):92-97.

DOI

YU J, ZHOU W W, LIU J Y. Numerical Analysis of the Performance of a Three Channel Intake Advanced Swirl Combustor[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2017, 37(4):92-97.

[15]
Tiller M M. Introduction to physical modeling with model-ica[M]. Holland: Kluwer Academic Publishers, 2001.

[16]
KUROSU A. YAMANISHI N. TANI N. et al. Study of next booster engine LE-X in JAXA[C]// 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento,California.Reston, Virigina:AIAA, 2006.

[17]
蒲光荣, 单磊, 赵晓慧, 等. 泵压式多次起动发动机起动过程仿真研究[J]. 火箭推进, 2019, 45(5):17-24.

PU G R, SHAN L, ZHAO X H, et al. Simulation study on start-up processes of a multi-startup turbopump-fed rocket engine[J]. Journal of Rocket Propulsion, 2019, 45(5):17-24.

[18]
张涛, 唐虎, 周江平, 等. 可贮存推进剂泵压式液体火箭发动机多次起动系统研究[J]. 火箭推进, 2010, 36(3):15-18.

ZHANG T, TANG H, ZHOU J P, et al. Study on the multi-start system of turbopump-fed rocket engine with storable propellants[J]. Journal of Rocket Propulsion, 2010, 36(3):15-18.

[19]
蔡国飙, 李家文, 田爱梅, 等. 液体火箭发动机设计[M]. 北京: 北京航空航天大学出版社, 2011:346-352.

CAI G B, LI J W, TIAN A, et al. Design of liquid rocket engines[M]. Beijing: Beihang University Press, 2011:346-318.

[20]
WYLIE E B, STREETER V L. Fluid transient in systems[M]. Endlewood Cliffs,US: Prentice Hall, 1993.

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