[1]王剑颖,梁海朝,吴限德,等.高超声速飞行器连续终端滑模姿态控制方法[J].哈尔滨工程大学学报,2016,37(02):187-191.[doi:10.11990/jheu.201411049]
 WANG Jianying,LIANG Haizhao,WU Xiande,et al.Continuous terminal sliding mode attitude control for hypersonic aircrafts[J].hebgcdxxb,2016,37(02):187-191.[doi:10.11990/jheu.201411049]
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高超声速飞行器连续终端滑模姿态控制方法(/HTML)
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《哈尔滨工程大学学报》[ISSN:1006-6977/CN:61-1281/TN]

卷:
37
期数:
2016年02期
页码:
187-191
栏目:
出版日期:
2016-02-25

文章信息/Info

Title:
Continuous terminal sliding mode attitude control for hypersonic aircrafts
作者:
王剑颖1 梁海朝2 吴限德3 付秋军1
1. 空间物理重点实验室, 北京 100076;
2. 北京航天长征飞行器研究所, 北京 100076;
3. 哈尔滨工程大学 航天与建筑工程学院, 黑龙江 哈尔滨 150001
Author(s):
WANG Jianying1 LIANG Haizhao2 WU Xiande3 FU Qiujun1
1. Science and Technology on Space Physics Laboratory, Beijing 100076, China;
2. Beijing Institute of Long March Vehicle, Beijing 100076, China;
3. College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China
关键词:
高超声速飞行器姿态控制终端滑模连续控制器有限时间鲁棒性
分类号:
V448.22
DOI:
10.11990/jheu.201411049
文献标志码:
A
摘要:
针对高超声速飞行器的姿态控制问题,考虑系统模型不确定性以及外界干扰的影响,基于快速终端滑模设计了连续的姿态跟踪控制器。将飞行器姿态控制系统模型按时间尺度划分为快回路和慢回路,其中慢回路的控制器设计目标是给出期望角速度作为快回路的制导指令,快回路控制器的设计目标是给出系统需求的控制力矩。基于有限时间控制理论分别针对各回路设计了连续的快速终端滑模姿态控制器,通过严格的数学证明,该控制器可以在系统模型存在不确定性以及外界干扰的情况下,使得姿态跟踪误差在有限时间内收敛。仿真结果表明本文的控制算法可以在短时间内使飞行器的姿态角均以较高的精度收敛至期望状态,且三个方向的控制力矩曲线均变化平滑,无抖振现象产生。

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期:2014-11-16;改回日期:。
基金项目:国家863计划资助项目(2013AA122904);国家自然科学基金资助项目(61304237);黑龙江省自然科学基金资助项目(F2015032); 哈尔滨市青年科技创新人才基金资助项目(RC2013QN001007);黑龙江省博士后科研启动金资助项目(LBH-Q13042);中央高校基本科研业务费资助项目(HEUCFD1406).
作者简介:王剑颖(1988-),女,工程师,博士;吴限德(1979-),男,副教授,博士.
通讯作者:吴限德,E-mail:xiande_wu@163.com.
更新日期/Last Update: 2016-03-15