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论文:2013,Vol:31,Issue(4):590-595 |
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引用本文： |
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刘剑, 朱战霞, 马家瑨. 基于螺旋理论的航天器相对运动建模与控制[J]. 西北工业大学 |
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Liu Jian, Zhu Zhanxia, Ma Jiajin. Establishing Spacecraft's Relative Orbit and Attitude Coupling Dynamics Model Based on Screw Theory[J]. Northwestern polytechnical university |
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| 基于螺旋理论的航天器相对运动建模与控制 |
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| 刘剑1,2, 朱战霞1,2, 马家瑨1,2 |
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1. 西北工业大学 航天学院, 陕西 西安 710072;
2. 航天飞行动力学技术重点实验室, 陕西 西安 710072 |
| 摘要: |
| 应用螺旋理论对航天器相对轨道与姿态运动进行了研究。针对航天器相对运动过程中存在的姿态轨道耦合问题:基于刚体假设,推导建立了基于螺旋对偶式的航天器姿轨耦合相对运动模型;分析给出了航天器相对运动过程中姿态轨道的耦合效应;针对所建模型的强耦合、非线性特性,在控制律设计时采用了非线性前馈控制,最后进行了数值仿真,结果表明了该模型和控制律的有效性,可为工程应用提供参考。 |
| 关键词:
螺旋理论
螺旋对偶式
姿轨耦合
耦合控制
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| Establishing Spacecraft's Relative Orbit and Attitude Coupling Dynamics Model Based on Screw Theory |
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| Liu Jian1,2, Zhu Zhanxia1,2, Ma Jiajin1,2 |
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1. College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Aerospace Flight Dynamics Laboratory, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| Considering the strong coupling between the orbit and attitude of two spacecraft in relative motion, based on the assumption of rigid body dynamics and the screw theory, we deduce and establish their orbit and attitude coupling dynamics model and analyze the orbit and attitude coupling effect.Considering that the dynamics model is strongly coupled and nonlinear, we design its nonlinear feedforward control law, which has a good control precision and stability and is suitable for the short-distance and in-orbit operations that have time constrains.We simulate the effectiveness of the orbit and attitude coupling dynamics model and the nonlinear feedforward control law ;the simu-lation results, given in Fig.1 through 6, and their analysis show preliminarily that:(1) both the relative speed and angular speed of the two spacecraft converge to zero, there being no change in their relative position and attitude and the whole control process reaching the desired value within 200 seconds; (2) the orbit and attitude coupling model we thus designed can be used for spacecraft's short-range randezvous and the nonlinear feedforward control law can satisfy the precision requirements for in-orbit operations. |
| Key words:
convergence of numerical methods
design
dynamics
feedforward control
mathematical models
MATLAB
orbits
spacecraft
stability
screw theory
orbit and attitude coupling model
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| 收稿日期: 2012-10-23
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 刘剑(1987-),西北工业大学硕士研究生,主要从事飞行器动力学建模与控制研究。
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| 作者相关文章 |
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| 刘剑 在本刊中的所有文章 |
| 朱战霞 在本刊中的所有文章 |
| 马家瑨 在本刊中的所有文章 |
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