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可重复使用运载器变结构姿态控制算法设计 被引量:5
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作者 呼卫军 周军 《西北工业大学学报》 EI CAS CSCD 北大核心 2007年第1期92-96,共5页
详细介绍了混合使用气动舵面和反作用控制系统的变结构姿态控制系统的设计方法。该控制算法用于可重复使用运载器,对于具有高空域大马赫飞行、机动明显、通路间耦合严重的非线性不确定时为系统具有良好的控制精度和抗干扰鲁棒性。同时... 详细介绍了混合使用气动舵面和反作用控制系统的变结构姿态控制系统的设计方法。该控制算法用于可重复使用运载器,对于具有高空域大马赫飞行、机动明显、通路间耦合严重的非线性不确定时为系统具有良好的控制精度和抗干扰鲁棒性。同时基于可重复使用运载器空间飞行轨迹、使用执行机构特性等因素,进行数学模型和控制律的简化设计和相应处理。仿真结果初步显示了基于变结构设计的PLV姿态控制算法可以确保对指令精确、鲁棒和解耦的跟踪能力,姿态误差小于1°,姿态响应超调量小于5%。 展开更多
关键词 反作用控制系(RCS) 可重复使用运载器(RLV) 控制分配 变结构姿态控制
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动能拦截器的动态滑模变结构姿控规律设计 被引量:1
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作者 郭鸿武 郑志强 《战术导弹控制技术》 2005年第3期42-44,共3页
研究了动能拦截器的动态滑模变结构姿态控制规律的设计.首先,建立了系统的纵向姿态运动模型,然后利用滑模变结构控制理论设计了控制规律,最后在考虑发动机最小作用冲量的基础上对控制规律进行了改进.该控制规律简单易行,仿真表明了该控... 研究了动能拦截器的动态滑模变结构姿态控制规律的设计.首先,建立了系统的纵向姿态运动模型,然后利用滑模变结构控制理论设计了控制规律,最后在考虑发动机最小作用冲量的基础上对控制规律进行了改进.该控制规律简单易行,仿真表明了该控制规律的有效性. 展开更多
关键词 动能拦截器 动态滑模变结构姿态控制规律 纵向姿态运动模型 发动机 战术弹道导弹
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Adaptive variable structure control based on backstepping for spacecraft with reaction wheels during attitude maneuver 被引量:7
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作者 宋斌 马广富 李传江 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2009年第1期138-144,共7页
An adaptive variable structure control method based on backstepping is proposed for the attitude maneuver problem of rigid spacecraft with reaction wheel dynamics in the presence of uncertain inertia matrix and extern... An adaptive variable structure control method based on backstepping is proposed for the attitude maneuver problem of rigid spacecraft with reaction wheel dynamics in the presence of uncertain inertia matrix and external disturbances. The proposed control approach is a combination of the backstepping and the adaptive variable structure control. The cascaded structure of the attitude maneuver control system with reaction wheel dynamics gives the advantage for applying the backstepping method to construct Lyapunov functions. The robust stability to external disturbances and parametric uncertainty is guaranteed by the adaptive variable structure control. To validate the proposed control algorithm, numerical simulations using the proposed approach are performed for the attitude maneuver mission of rigid spacecraft with a configuration consisting of four reaction wheels for actuator and three magnetorquers for momentum unloading. Simulation results verify the effectiveness of the proposed control algorithm. 展开更多
关键词 rigid spacecraft attitude maneuver BACKSTEPPING variable structure control reaction wheel dynamic
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Variable structure attitude maneuver and vibration control of flexible spacecraft
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作者 胡庆雷 马广富 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2008年第5期705-710,共6页
A dual-stage control system design method is presented for the three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In... A dual-stage control system design method is presented for the three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In this design approach, the attitude control and the vibration suppression sub-systems are designed separately using the lower order model. The design of attitude controller is based on the variable structure control (VSC) theory leading to a discontinuous control law. This controller accomplishes asymptotic attitude maneuvering in the closed-loop system and is insensitive to the interaction of elastic modes and uncertainty in the system. To actively suppress the flexible vibrations, the modal velocity feedback control method is presented by using piezoelectric materials as additional sensor and actuator bonded on the surface of the flexible appendages. In addition, a special configuration of actuators for three-axis attitude control is also investigated: the pitch attitude controlled by a momentum wheel, and the roll/yaw control achieved by on-off thrusters, which is modulated by pulse width pulse frequency modulation technique to construct the proper control torque history. Numerical simulations performed show that the rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque and parameter uncertainty. 展开更多
关键词 variable structure control flexible spacecraft vibration control attitude maneuver
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