航天推进技术研究院主办
[1]朱丹波,南渭林,薛会建.基于专家控制系统的发动机
人口压力闭环控制方案[J].火箭推进,2009,35(03):42-46.
Zhu Danbo,Nan Weilin,Xue Huijian.Study on closed loop control of rocket engine inlet pressure based on expert control system[J].Journal of Rocket Propulsion,2009,35(03):42-46.
点击复制
Zhu Danbo,Nan Weilin,Xue Huijian.Study on closed loop control of rocket engine inlet pressure based on expert control system[J].Journal of Rocket Propulsion,2009,35(03):42-46.
基于专家控制系统的发动机 人口压力闭环控制方案
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
35
期数:
2009年03期
页码:
42-46
栏目:
测控与试验
出版日期:
2009-06-30
- Title:
- Study on closed loop control of rocket engine inlet pressure based on expert control system
- Keywords:
- liquid rocket engine; inlet pressure; expert control; valve matrix
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 液体火箭发动机在地面试验过程中，试车台推进剂供应系统必须保证发动机的 入12压力在任务要求的范围内，而目前采用压力继电器控制进气电磁阀来调节入口压力。这 种方式调节精度低。响应滞后。根据试车台增压系统的特点和增压系统开环控制数年所积累 的经验，提出基于专家控制思想和以孔板矩阵作为执行机构的压力闭环控制方案。该控制方 法无需精确的数学模型，又能按照设定的精度智能调节增压孔板矩阵。使发动机入口压力自 动跟随设定值而变化。
- Abstract:
- Inlet pressure of the liquid rocket engine should be controlled in a range by the propellant supplying system in the ground test．At present，the pressure is controlled by an electromagnetic valve which is driven by a pressure relay．But the regulation precision is low and the response hysteresis is significant．A new project is put forward in this paper which is based on the ex— pert control system and the experience of the open-loop control system during these years，the exec· utive is a series of valves．The virtue of the new project is that it does not need precision mathmatic model and the pressure will follow the set value well after controlling of the valve matrix in the design precision．
参考文献/References:
[l]蒋慰孙，俞金寿．过程控制工程[M]．北京：中国石化出版
社。1998．
[2]王顺晃，舒迪前．智能控制系统及其应用[M]．北京：机械
工业出版社。2005．
[3]邵惠鹤．工业过程高级控制[M]．上海：上海交通大学出
版社。1997．
[4]李异河，丁问司，孙海平．液压与气动技术[M]．北京：国
防工业出版社，2006．
相似文献/References:
[1]郑 伟,李护林,陈新红.激光快速成形技术在液体动力领域的应用前景[J].火箭推进,2015,41(06):1.
ZHENG Wei,LI Hulin,CHEN Xinhong.Application prospect of laser rapid prototyping
technology in the field of liquid power[J].Journal of Rocket Propulsion,2015,41(03):1.
[2]郭 敬,宋晶晶,孔凡超.发动机推进剂增压输送系统建模仿真技术综述[J].火箭推进,2015,41(05):1.
GUO Jing,SONG Jingjing,KONG Fanchao.Overview of modeling and simulation technology
for propellant pressurization feed system
of liquid rocket engine[J].Journal of Rocket Propulsion,2015,41(03):1.
[3]于 康,谢荣华,陈晓江.表面张力贮箱电子束焊接工艺研究[J].火箭推进,2015,41(05):89.
YU Kang,XIE Ronghua,CHEN Xiaojiang.Study on electron beam welding process
for surface tension tank[J].Journal of Rocket Propulsion,2015,41(03):89.
[4]刘中华,苏 晨,汪军安,等.气路膜片设计研究[J].火箭推进,2015,41(05):95.
LIU Zhonghua,SU Chen,WANG Junan,et al.Design and study of pneumatic diaphragm in gas circuit[J].Journal of Rocket Propulsion,2015,41(03):95.
[5]薛 薇,蔡震宇,曹红娟,等.基于可视化平台的液氢/液氧火箭发动机核心部件质量计算[J].火箭推进,2015,41(04):61.
XUE wei,CAI Zhenyu,CAO Hongjuan,et al.Mass calculation of key assembly units in
LH2/ LOX rocket engine based on visual interface[J].Journal of Rocket Propulsion,2015,41(03):61.
[6]穆朋刚,童 飞,蒲光荣,等.温度对贮箱增压系统的影响分析[J].火箭推进,2015,41(04):74.
MU Penggang,TONG Fei,PU Guangrong,et al.Influence of temperature on tank pressurization system[J].Journal of Rocket Propulsion,2015,41(03):74.
[7]高朝辉,刘 宇,肖 肖,等.垂直着陆重复使用运载火箭对动力技术的挑战[J].火箭推进,2015,41(03):1.
GAO Zhao-hui,LIU Yu,et al.Challenge to propulsion technology for vertical
landing reusable launch vehicle[J].Journal of Rocket Propulsion,2015,41(03):1.
[8]申智帅,等.气动增压器技术及其在空间推进系统的应用[J].火箭推进,2015,41(03):15.
SHEN Zhi-shuai,RUAN Hai-jun,et al.Pneumopump technology and its application
in space propulsion system[J].Journal of Rocket Propulsion,2015,41(03):15.
[9]张 翔,徐洪平,安雪岩,等.液体火箭发动机稳态运行故障
数据聚类分析研究0[J].火箭推进,2015,41(02):118.
ZHANG Xiang,XU Hong-ping,AN Xue-yan,et al.Clustering analysis for fault data in steady process of
liquid propellant rocket engine[J].Journal of Rocket Propulsion,2015,41(03):118.
[10]窦 唯,闫宇龙,金志磊,等.某发动机涡轮泵转子高温超速/疲劳试验研究[J].火箭推进,2015,41(01):15.
DOU Wei,YAN Yu-long,JIN Zhi-lei,et al.Fatigue experiment of turbo-pump rotor at
over-speed and high temperature condition[J].Journal of Rocket Propulsion,2015,41(03):15.
备注/Memo
收稿日期：2008—11—1l；修回日期：2008一ll一23。 作者简介：朱丹波(1981一)，女，工程师。研究领域为液体火箭发动机试验控制技术。
更新日期/Last Update:
1900-01-01