Reconfiguration control of launch vehicle based on Armijo criterion and BFGS algorithm

Haisen YU; Shujun TAN; Zhigang WU

doi:10.13224/j.cnki.jasp.20210059

Chinese

您当前的位置：

首页 >

文章列表页 >

Reconfiguration control of launch vehicle based on Armijo criterion and BFGS algorithm

Rocket Engine | 更新时间：2025-04-07

- Reconfiguration control of launch vehicle based on Armijo criterion and BFGS algorithm
- Journal of Aerospace Power Vol. 37, Issue 1, Pages: 204-213(2022)
- 作者机构：
  
  1.大连理工大学工业装备结构分析国家重点实验室，辽宁大连 116023
  2.大连理工大学辽宁省空天飞行器前沿技术重点实验室，辽宁大连 116023
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210059
  CLC：
- 稿件说明：
移动端阅览
Haisen YU, Shujun TAN, Zhigang WU. Reconfiguration control of launch vehicle based on Armijo criterion and BFGS algorithm[J]. Journal of Aerospace Power, 2022, 37(1): 204-213.
DOI：

Haisen YU, Shujun TAN, Zhigang WU. Reconfiguration control of launch vehicle based on Armijo criterion and BFGS algorithm[J]. Journal of Aerospace Power, 2022, 37(1): 204-213. DOI： 10.13224/j.cnki.jasp.20210059.

摘要

以某型运载火箭为研究对象，研究了伺服机构故障下的重构控制问题。将该问题转化为有约束二次规划问题，采用一种Armijo准则和BFGS算法相结合的控制分配方法来求解。Armijo准则可以保证优化算法的收敛性，而BFGS算法则避免了迭代过程对Hesse阵的求逆运算，且具有收敛快的优点。将该重构方法与不动点迭代算法进行了对比，该算法经过8次迭代收敛，目标函数值和误差值分别收敛到

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242517&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242513&type=

4.06400013

2.62466669

量级左右和

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242525&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242521&type=

5.67266655

2.62466669

量级；而不动点迭代算法经过30次迭代尚未完全收敛，目标函数值和误差分别收敛到

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242531&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242528&type=

4.06400013

2.62466669

量级左右和

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242540&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242536&type=

5.67266655

2.62466669

量级。结果表明该重构方法比不动点迭代算法收敛快且收敛精度高。以单台发动机发生卡死故障为例对该方法进行了仿真验证，得到了与无故障情况下相同的控制效果，验证了该重构方法的有效性和正确性。

Abstract

Taking a new type of launch vehicle as the research object，the problem of reconfiguration control under servo mechanism fault was studied.The problem was transformed into a constrained quadratic programming problem，and then a control allocation method combining the Armijo criterion and BFGS algorithm was used to solve the problem.Armijo criterion can ensure the convergence of the optimization algorithm，while BFGS algorithm avoided the inversion of Hesse matrix in the iterative process，and had the advantage of fast convergence.The proposed reconstruction method was compared with the fixed point iterative algorithm.After 8 iterations，the objective function value and error value converged to about

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242546&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242543&type=

4.82600021

3.04800010

magnitude and

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242554&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242549&type=

6.60400009

3.04800010

magnitude，respectively.However，the fixed point iterative algorithm was not completely converged after 30 iterations，and the objective function value and error converged to about

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242562&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242558&type=

4.82600021

3.04800010

magnitude and

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242569&type=

http://html.publish.founderss.cn/rc-pub/api/common/picture?pictureId=24242565&type=

6.60400009

3.04800010

magnitude，respectively.The results showed that the reconstruction method converged faster and had higher convergence precision than the fixed point iterative algorithm.Taking a single engine stuck fault as an example，the simulation results showed that the control effect was the same as that in the case of no fault，which verified the validity and correctness of the proposed method.

关键词

Keywords

references

冯昊 , 李新明 , 潘豪 . 大推力运载火箭控制系统控制力重构技术研究 [J]. 载人航天 , 2012 , 18 （ 6 ）: 75 ⁃ 79 .

FENG Hao , LI Xinming , PAN Hao . On reconstruction technologies of thrusting force for heavy thrust launch vehicles ［J]. Chinese Journal of Manned Spaceflight , 2012 , 18 （ 6 ）: 75 ⁃ 79 . （in Chinese）

朱心中 . 基于控制分配的多操纵面飞行器重构控制研究 [D]. 南京：南京航空航天大学 , 2011 .

ZHU Xinzhong . Study of reconfigurable control based on control allocation for aircraft with multiple effectors [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2011 . （in Chinese）

段文杰 , 王大轶 , 刘成瑞 . 一种闭环冗余系统可重构控制方法 [J]. 空间控制技术与应用 , 2014 , 40 （ 6 ）: 21 ⁃ 25，47 .

DUAN Wenjie , WANG Dayi , LIU Chengrui . A reconfigurable control method for over⁃actuated closed⁃loop systems [J]. Aerospace Control and Application , 2014 , 40 （ 6 ）: 21 ⁃ 25，47 . （in Chinese）

姬猛 . 推力不对称时民机飞行控制律重构技术研究 [D]. 南京：南京航空航天大学 , 2011 .

JI Meng . Research on control law reconfiguration for civil aircraft with asymmetric thrust [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2011 . （in Chinese）

张亮 , 傅俊勇 , 刘洪宇 . 伺服机构反馈故障仿真与分析 [J]. 液压与气动 , 2014 （ 5 ）: 122 ⁃ 125 .

ZHANG Liang , FU Junyong , LIU Hongyu . Simulation and analysis of servomechanism with feedback failure [J]. Hydraulic and Pneumatic , 2014 （ 5 ）: 122 ⁃ 125 . （in Chinese）

程堂明 , 李家文 , 陈宇，等 . 运载火箭伺服机构故障检测与诊断的扩展多模型自适应方法 [J]. 国防科技大学学报 , 2017 , 39 （ 5 ）: 80 ⁃ 89 .

CHENG Tangming , LI Jiawen , CHEN Yu , et al . Extended multiple model adaptive method for fault detection and diagnosis of launch vehicle's servo mechanism [J]. Journal of National University of Defense Technology , 2017 , 39 （ 5 ）: 80 ⁃ 89 . （in Chinese）

尹彪 , 刘磊 , 王永骥 . 火箭姿态控制与故障重构的研究［C］∥ 中国自动化学会中南六省（区）第28届年会论文集 . 广州：中南六省区（广东、广西、湖南、湖北、河南、海南）自动化学， 2010 : 241 ⁃ 245 ．

崔玉伟 , 章卫国 , 李广文 , 等 . 基于线性规划的多操纵面重构控制研究 [J]. 飞行力学 , 2011 , 29 （ 2 ）: 41 ⁃ 44 .

CUI Yuwei , ZHANG Weiguo , LI Guangwen , et al . Research for multi⁃control⁃effector reconfigurable control based on linear programming [J]. Flight Dynamics , 2011 , 29 （ 2 ）: 41 ⁃ 44 . （in Chinese）

程堂明 , 陈宇 . 适应伺服机构卡死故障的控制指令重分配技术研究 [J]. 导弹与航天运载技术 , 2017 , 1 （ 1 ）: 51 ⁃ 55 .

CHENG Tangming , CHEN Yu . Research on reconfigurable control allocation technology under stuck actuator failures [J]. Missiles and Space Vehicles , 2017 , 1 （ 1 ）: 51 ⁃ 55 . （in Chinese）

孟州 . 发动机伺服机构故障下大型捆绑火箭容错控制 [D]. 长沙：国防科技大学 , 2013 .

MENG Zhou . Fault tolerant control for large strap⁃on launch vehicle's servomechanism [D]. Changsha : National University of Defense Technology , 2013 . （in Chinese）

程堂明 , 李家文 , 唐国金 . 伺服机构故障下基于线性规划的运载火箭姿控系统重构控制 [J]. 国防科技大学学报 , 2017 , 39 （ 1 ）: 51 ⁃ 57 .

CHENG Tangming , LI Jiawen , TANG Guojin . Reconstruction of attitude control system of launch vehicle based on linear programming under servo mechanism fault [J]. Journal of National University of Defense Technology , 2017 , 39 （ 1 ）: 51 ⁃ 57 . （in Chinese）

TJØNNÅS J . Nonlinear and adaptive dynamic control allocation [D]. Trondheim,Norwegian : Norwegian University of Science and Technology , 2008 .

JOHANSEN T A , FOSSEN T I . Control allocation：a survey [J]. Automatica , 2013 , 49 （ 5 ）: 1087 ⁃ 1103 .

SILVA A G , LEITE FILHO W C . Launch vehicle attitude control system using PD plus phase lag [J]. IFAC Proceedings Volumes , 2013 , 46 （ 19 ）: 48 ⁃ 53 .

JEE G , BRINDA V , LALITHAMBIKA V R , et al . Influence of accelerometer location on autopilot stability of reusable launch vehicle attitude control system [J]. IFAC Proceedings Volumes , 2014 , 47 （ 1 ）: 205 ⁃ 210 .

黄盘兴 . 重型运载火箭可重构控制系统设计研究 [D]. 哈尔滨：哈尔滨工业大学 , 2012 .

HUANG Panxing . Research on reconfigurable control system design of heavy launch vehicle [D]. Harbin : Harbin Institute of Technology , 2012 . （in Chinese）

张宁 , 章卫国 , 李广文 . 一种基于BFGS算法的二次规划控制分配算法 [J]. 飞行力学 , 2013 , 31 （ 6 ）: 508 ⁃ 511 .

ZHANG Ning , ZHANG Weiguo , LI Guangwen . A method of quadratic programming control allocation based on BFGS algorithm [J]. Flight Dynamics , 2013 , 31 （ 6 ）: 508 ⁃ 511 . （in Chinese）

孙清滢 , 刘新海 . 结合广义Armijo步长搜索的一类新的共轭度算法及其收敛特征 [J]. 工程数学学报 , 2003 , 20 （ 1 ）: 14 ⁃ 20 .

SUN Qingying , LIU Xinhai . Global convergence results for a new conjugate gradient method with generalized Armijo step size rule [J]. Chinese Journal of Engineering Mathematics , 2003 , 20 （ 1 ）: 14 ⁃ 20 . （in Chinese）

刘建国 , 葛仁东 , 夏尊铨 , 等 . 非凸函数极小问题的BFGS算法 [J]. 运筹与管理 , 2004 , 13 （ 2 ）: 62 ⁃ 65 .

LIU Jianguo , GE Rendong , XIA Zunquan , et al . BFGS algorithm for sloving minimum problem of nonconvex function [J]. Operations Research and Management Science , 2004 , 13 （ 2 ）: 62 ⁃ 65 . （in Chinese）

李家文 . 大型捆绑火箭姿态控制系统的建模、设计与分析 [D]. 长沙：国防科学技术大学 , 2011 .

LI Jiawen . Modeling design and analysis of large strap⁃on launch vehicle's attitude control system [D]. Changsha : National University of Defense Technology , 2011 . （in Chinese）

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Heat transfer prediction on film boiling of liquid hydrogen under normal gravity and microgravity environments

On-orbit refilling technologies and schemes of liquid propellant

Investigation on acquisition schemes of cryogenic propellant subcooling for long-term on-orbit storage

Rapid optimization design of ascent rendezvous trajectory for launch vehicles based on hybrid particle swarm algorithm

考虑多源不确定性的复合材料风扇叶片高周疲劳失效概率评估

Related Author

张大巧

凌王辉

刘凯

鲜勇

王磊

朱康

马原

谢福寿

Related Institution

火箭军工程大学空间工程系

西安交通大学能源与动力工程学院制冷与低温工程系

航天低温推进剂技术国家重点实验室

School of Energy and Power Engineering, Xi'an Jiaotong University

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰