薄膜天线航天器刚-柔-热耦合动力学建模与复合控制研究

陈呈; 刘翔

doi:10.21656/1000-0887.450094

薄膜天线航天器刚-柔-热耦合动力学建模与复合控制研究

doi: 10.21656/1000-0887.450094

陈呈^1,,
刘翔^{1, 2, ,}

1.
上海交通大学工程力学系，上海 200240
2.
上海交通大学重庆研究院，重庆 401122

基金项目:

国家自然科学基金 12102252

国家自然科学基金 12172214

12172214 CSTB2023NSCQ-MSX0761

详细信息

作者简介:
陈呈(2001—)，男，硕士生(E-mail: cc2821619240@sjtu.edu.cn)

通讯作者:
刘翔(1993—)，男，助理研究员，博士，硕士生导师(通讯作者. E-mail: codyxiang@sjtu.edu.cn)

中图分类号: TU311.3;TU352.1
计量
- 文章访问数: 91
- HTML全文浏览量: 42
- PDF下载量: 20
- 被引次数: 0
出版历程
- 收稿日期: 2024-04-11
- 修回日期: 2024-05-09
- 刊出日期: 2025-03-01

Rigid-Flexible-Thermal Coupling Dynamic Modeling and Hybrid Control of Membrane Antenna Spacecraft

CHEN Cheng^1
,,
LIU Xiang^{1, 2
, ,}

1.
Department of Engineering Mechanics, Shanghai Jiao Tong University, Shanghai 200240, P.R.China
2.
Chongqing Research Institute, Shanghai Jiao Tong University, Chongqing 401122, P.R.China

摘要

摘要: 大型空间薄膜天线在深空探测、天基预警、对地观测等领域具有广阔的应用前景.由于薄膜天线具有大、轻、柔的显著特征，其动力学与控制问题十分复杂且突出.与此同时，由于天线工作性能的需求，天线在轨运行时必须保持极高的指向精度和形面精度.这就要求我们对薄膜航天器进行精细的动力学分析与有效的主动控制设计.该文针对一类平面张拉式薄膜天线进行刚-柔-热耦合动力学建模与复合控制问题的研究.首先，基于非线性有限元方法建立了薄膜天线结构的非线性动力学模型，并对该模型进行了模型降阶.然后，基于非线性降阶模型并考虑空间热环境的影响，采用混合坐标法建立了航天器的刚-柔-热耦合动力学模型.最后，采用合力合成控制方法结合拉索作动的非线性振动控制策略，对航天器的姿态运动和非线性振动进行了同步、复合控制.
- 薄膜天线 /
- 刚-柔-热耦合动力学建模 /
- 非线性振动 /
- 复合控制
Abstract: Large space membrane antenna has a great prospect in the fields of deep space exploration, space-based early warning and earth observation. Due to the large-size and high-flexibility of the membrane structure, the membrane antenna spacecraft poses challenging dynamic and control issues. Meanwhile, to maintain the working performance of the antenna, the pointing accuracy and surface accuracy must be kept strictly. Therefore, accurate dynamic modeling and effective active control of large membrane antenna are of great significance and practical interest, and attract a lot of attentions in recent years. The rigid-flexible-coupling dynamics and hybrid control of membrane antenna spacecraft were studied. First, based on the nonlinear finite method the nonlinear dynamic model for the membrane antenna structure was established, and the nonlinear dynamic model order reduction was also studied. Then, in view of the thermal flux, the rigid-flexible-thermal coupling dynamic model for the spacecraft was established by means of the hybrid coordinate method. With the component synthesis vibration suppression method and the cable-actuator-based nonlinear vibration control method, a hybrid control system was designed to control the attitude motion meanwhile reduce the nonlinear vibration.
- membrane antenna /
- rigid-flexible-thermal coupling dynamic modeling /
- nonlinear vibration /
- hybrid control

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图 1 薄膜天线航天器

Figure 1. The membrane antenna spacecraft

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图 2 薄膜天线航天器在轨热环境

Figure 2. The heat flux for the orbiting membrane antenna

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图 3 薄膜天线航天器坐标系统示意图

Figure 3. Coordinate systems of the membrane antenna spacecraft

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图 4 薄膜天线航天器姿态-振动复合控制

Figure 4. The hybrid control system for the membrane antenna spacecraft

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图 5 时间-燃料最优控制输入

Figure 5. The time-fuel optimal control

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图 6 分力合成控制方法

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 6. The component synthesis vibration suppression method

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图 7 薄膜天线姿态机动过程中的温度变化

Figure 7. Temperatures of the membrane antenna during attitude maneuvering

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图 8 仅在时间-燃料最优控制输入下薄膜天线航天器的刚-柔耦合系统动力学响应

Figure 8. Rigid-flexible coupling dynamic responses of the membrane antenna spacecraft under time-fuel optimal control

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图 9 薄膜天线航天器分力合成控制力矩

Figure 9. Attitude control input obtained with the component synthesis vibration suppression method

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图 10 脉冲宽度调制后的薄膜天线航天器分力合成控制输入

Figure 10. Attitude control input after pulse width modulation

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图 11 复合控制下薄膜天线航天器的刚-柔耦合系统动力学响应

Figure 11. Rigid-flexible coupling dynamic responses of the membrane antenna spacecraft under the proposed hybrid control method

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表 1 薄膜天线航天器材料参数

Table 1. Material parameters of thin-film antenna spacecraft

part	material property	value
satellite	length /m	1
	width /m	1
	height /m	1
	mass /kg	150
membrane array	Young’s modulus /GPa	3.5
	Poisson’s ratio	0.34
	density /(kg/m³)	1 530
	length /m	23.4
	width /m	5.6
	thickness /m	0.000 25
support frame	Young’s modulus /GPa	40
	Poisson’s ratio	0.3
	density /(kg/m³)	1 800
	length /m	24
	width /m	7
	cross-sectional area /m²	0.000 318
	moment of inertia of the z-axis /m⁴	0.000 001 26
	moment of inertia of the y-axis /m⁴	0.000 000 37
tension cable	Young’s modulus /GPa	133
	Poisson’s ratio	0.36
	density /(kg/m³)	1 440
	cross-sectional area /m²	0.000 000 049
	tensioning force in the x axis direction /N	50
	tensioning force in the y axis direction /N	50
tension pole	Young’s modulus /GPa	210
	Poisson’s ratio	0.3
	density /(kg/m³)	1 800
	length /m	7
	cross-sectional area /m²	0.000 178
	moment of inertia of the z-axis /m⁴	0.000 000 012 5
	moment of inertia of the y-axis /m⁴	0.000 000 012 5

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