大挠性机动飞行器改进型正向位置反馈振动控制

袁秋帆; 霍明英; 齐乃明; 曹世磊; 肖余之

doi:10.13700/j.bh.1001-5965.2017.0101

大挠性机动飞行器改进型正向位置反馈振动控制

doi: 10.13700/j.bh.1001-5965.2017.0101

1.
哈尔滨工业大学航天学院, 哈尔滨 150001
2.
上海航天技术研究院, 上海 201109

基金项目:

国家自然科学基金 11672093

航天科技集团-哈尔滨工业大学联合技术创新项目

详细信息

作者简介:
袁秋帆  男, 博士研究生。主要研究方向:飞行器大挠性结构主动振动控制

霍明英  男, 博士, 助理研究员。主要研究方向:超大型空间结构动力学建模及试验研究

齐乃明  男, 博士, 教授, 博士生导师。主要研究方向:超大型空间结构动力学建模及试验研究

通讯作者:
霍明英, E-mail:huomingying@hit.edu.cn

中图分类号: V414.3⁺3;TB123
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- 文章访问数: 902
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- 被引次数: 2
出版历程
- 收稿日期: 2017-02-27
- 录用日期: 2017-03-17
- 网络出版日期: 2018-02-20

Vibration control for large flexible maneuvering spacecraft using modified positive position feedback

1.
School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
2.
Shanghai Academy of Spaceflight Technology, Shanghai 201109, China

Funds:

National Natural Science Foundation of China 11672093

Aerospace Technology Group-Harbin Institute of Technology Joint Technical Innovation Project

More Information

Corresponding author: HUO Mingying, E-mail:huomingying@hit.edu.cn

摘要

摘要:
针对一类大挠性机动飞行器，同时进行的姿态和轨道机动将激发挠性结构与中心刚体之间的平移耦合模态和转动耦合模态。为了提高姿态和轨道控制稳定度，提出了一种整合的改进型正向位置反馈（MPPF）控制方法抑制挠性结构的振动。首先建立了包含转动耦合和平移耦合模态的动力学模型，推导了耦合模态参数，然后基于MPPF控制律，设计了对转动耦合模态和平移耦合模态同时进行抑制的主动振动控制器，并采用M范数方法进行了参数优化，采用压电智能材料构建了主动振动控制系统。仿真结果表明所设计的控制器能够对机动飞行器的挠性结构振动起到很好的抑制效果，并且提高了姿态和轨道的控制稳定度。
- 挠性飞行器 /
- 机动 /
- 振动控制 /
- 耦合动力学 /
- 改进型正向位置反馈(MPPF)
Abstract:
Considering maneuvering spacecraft with high flexible appendages, the translational and rotational coupling vibration modes between flexible structures and center rigid body are excited by the simultaneous attitude and orbit maneuvering. Aimed at higher stability of attitude and orbit control of spacecraft, an integrated modified positive position feedback (MPPF) controller is proposed to suppress the vibration of flexible structure. First, dynamic model is established with translational and rotational coupling effects considered, and coupling mode parameters are calculated. Then, an integrated controller was designed to suppress the translational and rotational coupling vibration modes based on MPPF. Controller parameters were optimized through M-norm optimization method. Active vibration control system is constructed using piezoelectric smart material. The simulation results show that the proposed controller is efficient on vibration suppression of the flexible structures and the stability of attitude and orbit control of maneuvering spacecraft is improved.
- flexible spacecraft /
- maneuvering /
- vibration control /
- coupling dynamics /
- modified positive position feedback (MPPF)

HTML全文

图 1 带有双侧对称帆板的飞行器模型

Figure 1. Spacecraft model with two-side symmetric solar planes

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图 2 飞行器整体的耦合模态振型^[14-15]

Figure 2. Global coupling model shape of spacecraft^[14-15]

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图 3 压电元件基本配置

Figure 3. Basic configuration of piezoelectric elements

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图 4 挠性结构弯曲引起压电片应变

Figure 4. Strain of piezoelectric elements caused by bending of flexible structure

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图 5 仿真配置

Figure 5. Simulation configuration

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图 6 系统幅频响应曲线

Figure 6. System amplitude frequency response curves

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图 7 Z向速度(算例1)

Figure 7. Z-direction velocity (Example 1)

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图 8 X轴角速度(算例1)

Figure 8. X-axis angular velocity (Example 1)

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图 9 帆板根部力矩(算例1)

Figure 9. Solar plane root moment (Example 1)

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图 10 帆板根部力矩的FFT变换(算例1)

Figure 10. FFT transform of solar plane root moment (Example 1)

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图 11 传感器采集电压(算例1)

Figure 11. Sensor voltage (Example 1)

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图 12 执行器输入电压(算例1)

Figure 12. Actuator input voltage(Example 1)

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图 13 Z向速度(算例2)

Figure 13. Z-direction velocity (Example 2)

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图 14 X轴角速度(算例2)

Figure 14. X-axis angular velocity (Example 2)

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图 15 帆板根部力矩(算例2)

Figure 15. Solar plane root moment (Example 2)

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图 16 帆板根部力矩的FFT变换(算例2)

Figure 16. FFT transform of solar plane root moment (Example 2)

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图 17 传感器采集电压(算例2)

Figure 17. Sensor voltage (Example 2)

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图 18 执行器输入电压(算例2)

Figure 18. Actuator input voltage (Example 2)

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