|本期目录/Table of Contents|

[1]王建华,刘鲁华,赵暾,等.带落角约束的超声速飞行器制导控制一体化设计[J].电机与控制学报,2017,21(02):76-86.[doi:10.15938/j.emc.2017.02.010]
 WANG Jian-hua,LIU Lu-hua,ZHAO Tun,et al.Integrated guidance and control design for supersonic vehicles with impact angle constraint [J].,2017,21(02):76-86.[doi:10.15938/j.emc.2017.02.010]
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《电机与控制学报》[ISSN:1007-449X/CN:23-1 408/TM]

卷:
21
期数:
2017年02
页码:
76-86
栏目:
出版日期:
2017-02-01

文章信息/Info

Title:
Integrated guidance and control design for supersonic vehicles with impact angle constraint


作者:
王建华刘鲁华赵暾汤国建
?(国防科学技术大学航天科学与工程学院,湖南长沙410073)
Author(s):
?WANG Jian-hua LIU Lu-hua ZHAO Tun TANGGuo-jian
?(College of Aerospace Science and Engineering National University of Defense Technology Changsha 410073,China)
关键词:
制导控制一体化 块动态面控制 输出调节 落角约束 超声速飞行器
Keywords:
integrated guidance and control block dynamic surface control output tuningimpact angle constraint supersonic vehicles
分类号:
V 448.2
DOI:
10.15938/j.emc.2017.02.010
文献标志码:
A
摘要:
针对超声速飞行器末飞行段攻击地面移动目标问题,提出一种带落角约束的制导控制一体化设计方法。联立目标-飞行器三维相对运动方程和飞行器控制系统非线性模型,基于不确定项有界假设建立具有严格反馈形式的制导控制一体化设计模型,将制导控制一体化设计问题转化为高阶非线性时变系统输出调节问题。构建视线角速率动态面向量并利用高频率反馈鲁棒控制方法得到控制系统的虚拟控制量,进而利用块动态面控制方法得到带落角约束的一体化制导控制律。以动态面和滤波误差为基础构建李雅普诺夫函数并证明各动态面和滤波误差的一致有界性。仿真结果表明,该一体化方法能保证飞行器以期望落角精确命中地面移动目标,且飞行器全部状态变量均有界稳定。
Abstract:
?According to the requirements of the supersonic vehicle which attacks the maneuver target with specified impact angle an integrated guidance and control(IGC) scheme considering impact angle con-straint is proposed. An intact IGC design model witli the strict feedback form was formulated by combining the three dimensional^ 3D) relative dynamics and nonlinear rotational dynamics of tlie supersonic ve-hicle under tlie assumption that tlie uncertainties in the IGC design model are bounded,and the IGC design problem was converted into an output tuning problem. The pseudo-inputs with respect to rotational loop of t!ie vehicle were obtained based on the blocl^ dynamic surface vector composed of elevation and azi-muth angle rates of t!ie line-of-sight( LOS) and the commanded control surface fin deflections were derived with the help of block dynamic surface control approach. Finally the states of the closed-loop system and the filter errors were proved to be with uniform ultimate boundedness based on the Lyapunov stability theor. Numerical simulation results show that the proposed IGC scheme can ensure an accuracy interception with desirable impact angle and the state varidbles of the supersonic vehicle are all bounde and stable

参考文献/References:

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相似文献/References:

[1]尹永鑫,杨明,王子才.导弹三维制导控制一体化设计[J].电机与控制学报,2010,(03):87.
 YIN Yong-xin,YANG Ming,WANG Zi-cai.Three-dimensional guidance and control for missile[J].,2010,(02):87.

备注/Memo

备注/Memo:
收稿日期: 2015-01-06
基金项目:国家专项工程基础理论研究(1502010507008);国防科学技术大学科研计划项目(重大应用基础研究,ZDYYJCYJ20140101)
作者简介:王建华(1988—),男,博士,研究方向为飞行动力学、制导与控制;
刘鲁华(1977—),男,博士,副教授,研究方向为飞行动力学、制导与控制;
赵暾(1989—),男,博士,研究方向为飞行动力学、制导与控制;
汤国建(1964—),男,博士,教授,博士生导师,研究方向为飞行动力学、制导与控制。
更新日期/Last Update: 2017-03-30