Spacecraft attitude control a linear matrix inequality approach
正版保障 假一赔十 可开发票
￥ 134.43 6.7折 ￥ 200 全新
库存2件
作者刘闯
出版社中国科技出版传媒股份有限公司
ISBN9787030719782
出版时间2021-06
装帧平装
开本其他
定价200元
货号11633399
上书时间2025-01-03
商品详情
- 品相描述：全新
- 商品描述
-
目录
Contents
Preface
1. Introduction of basic knowledge
1.1 Linear matrix inequalities
1.1.1 What are linear matrix inequalities?
1.1.2 Useful lemmas for linear matrix inequalities
1.1.3 Advantages of linear matrix inequalities
1.1.4 Some standard linear matrix inequalitie problems
1.2 Spacecraft attitude kinematics and dynamics
1.2.1 Attitude representations
1.2.2 Attitude kinematics
1.2.3 Attitude dynamics
References
2. State feedback nonfragile control
2.1 Introduction
2.2 Problem formulation
2.2.1 Attitude dynamics modeling
2.2.2 Control objective
2.3 State feedback nonfragile control law
2.3.1 Some lemmas
2.3.2 Sufficient conditions under additive perturbation
2.3.3 Sufficient conditions under multiplicative perturbation
2.4 Simulation test
2.4.1 Simulation results under additive perturbation
2.4.2 Simulation results under multiplicative perturbation
2.4.3 Simulation results using a mixed H2/HN controller
2.5 Conclusions
References
3. Dynamic output feedback nonfragile control
3.1 Introduction
3.2 Problem formulation
3.2.1 Attitude system description
3.2.2 Nonfragile control problem
3.2.3 Control objective
3.3 Dynamic output feedback nonfragile control law design
3.3.1 Some lemmas
3.3.2 Controller design under additive perturbation
3.3.3 Controller design under multiplicative perturbation
3.3.4 Controller design under coexisting additive and multiplicative perturbations
3.4 Simulation test
3.4.1 Simulation results under additive perturbation
3.4.2 Simulation results under multiplicative perturbation
3.4.3 Simulation results under coexisting additive and multiplicative perturbations
3.5 Conclusions
References
4. Observer-based fault tolerant delayed control
4.1 Introduction
4.2 Problem formulation
4.2.1 Attitude system description
4.2.2 Control objective
4.3 Observer-based fault tolerant control scheme
4.3.1 Intermediate observer design
4.3.2 Delayed controller design
4.3.3 Control solution
4.4 Simulation test
4.4.1 Simulation results using the proposed controller
4.4.2 Simulation results using the prediction-based sampled-dataHN controller
4.4.3 Comparison analysis using different controllers
4.5 Conclusions
References
5. Observer-based fault tolerant nonfragile control
5.1 Introduction
5.2 Problem formulation
5.2.1 Attitude system description
5.2.2 Stochastically intermediate observer design
5.2.3 Nonfragile controller design
5.2.4 Control objective
5.3 Feasible solution for both cases
5.3.1 Some lemmas
5.3.2 Sufficient conditions under additive perturbation
5.3.3 Sufficient conditions under multiplicative perturbation
5.4 Simulation test
5.4.1 Comparison analysis under additive perturbation
5.4.2 Comparison analysis under multiplicative perturbation
5.5 Conclusions
References
6. Disturbance observer-based controlwith input MRCs
6.1 Introduction
6.2 Problem formulation
6.2.1 Attitude system description
6.2.2 Control objective
6.3 Controller design and analysis
6.3.1 Some lemmas
6.3.2 Coexisting conditions for observer and controller gains
6.3.3 Proof and analysis
6.4 Simulation test
6.4.1 Nonzero angular rates
6.4.2 Zero angular rates
6.4.3 Evaluation indices for the three conditions
6.4.4 Parametric influence on control performance
6.5 Conclusions
References
7. Improved mixed H2/HN control with poles assignment constraint
7.1 Introduction
7.2 Problem formulation
7.2.1 Flexible spacecraft dynamics with two bending modes
7.2.2 HN and H2 performance constraint
7.2.3 Poles assignment
7.2.4 Control objective
7.3 Improved mixed H2/HN control law
7.3.1 Some
内容摘要
本书凝聚了作者在航天器姿态控制领域近十年的原创性研究成果，系统研究了多源复杂扰动下姿态稳定控制方法。全书共11章。第1章对线性矩阵不等式方法与航天器姿态动力学进行了介绍，为后续控制系统设计奠定理论基础；第2—6章介绍了刚体航天器姿态稳定控制方法，主要包括：状态反馈非脆弱控制、动态输出反馈非脆弱控制、基于中间状态观测器的容错时滞控制与容错非脆弱控制，以及基于干扰观测器的输入受限控制；第7—9章介绍了柔性航天器姿态稳定控制方法，主要包括：具有极点配置约束的改进混合H2/H∞控制、非脆弱H∞控制，以及基于主动振动抑制的抗干扰控制；第10章介绍了航天器混沌姿态同步跟踪控制方法，并在第11章给出了欠驱动混沌姿态角速度稳定控制方法供读者参考。本书可供航空航天、机械电子及控制相关专业的高等院校本科生和研究生学习参考，也是相关领域科研工作者和工程技术人员查阅或教学的有效工具。
精彩内容
本著作针对航天器姿态控制系统存在的诸多扰动问题，基于线性矩阵不等式（LMI）方法对该系统的多目标优化控制问题进行详细分析及理论研究。航天器姿态控制精度及稳定度与终端小角度姿态机动关系密切，且极易受模型参数不确定性、控制器增益摄动、执行机构故障、输入受限及输入时延等诸多因素影响。LMI方法具有三方面优势：全局很优解和数值可靠性、多目标优化设计和成熟软件包，在稳定性及控制领域是很好有效。本著作凝聚了作者近十年的原创性研究成果，将刚体和柔性航天器姿态控制系统模型进行归一化处理，基于此融合LMI方法进行一系列针对具体问题的控制算法研究。
相关推荐
-
Spacecraft Attitude Dynamics
九五品西安
￥ 400.00
-
Fundamentals of Spacecraft Attitude Determination and Control
八五品北美洲
￥ 1899.00
-
Spacecraft attitude control a linear matrix inequality approach9787030719782
全新广州
￥ 158.00
-
Fundamentals of Spacecraft Attitude （影印版） （书脊有破损）
八五品大连
￥ 200.00
-
spacecraft Attitude Determination and control 航天器姿态确定与控制
九品北京
￥ 900.00
-
【假一罚四】Spacecraft attitude control a linear matrix inequality approach
全新嘉兴
￥ 136.20
-
Spacecraft Attitude Dynamics，航天器姿态动力学，英文原版
九五品西安
￥ 299.00
-
SPACECRAFT
八五品苏州
￥ 50.00
-
SPACECRAFT
八品惠州
￥ 1888.88
-
Attitude
九品北京
￥ 200.00
— 没有更多了 —
以下为对购买帮助不大的评价