| 引用本文: | 葛东明,史纪鑫,邹元杰,邓润然,朱卫红.深空探测柔性太阳帆航天器动力学建模与姿态控制[J].控制理论与应用,2019,36(12):2019~2027.[点击复制] |
| GE Dong-ming,SHI Ji-xin,ZOU Yuan-jie,DENG Run-ran,ZHU Wei-hong.Dynamic modeling and attitude control of flexible solar sail spacecraft for deep space exploration[J].Control Theory and Technology,2019,36(12):2019~2027.[点击复制] |
|
| 深空探测柔性太阳帆航天器动力学建模与姿态控制 |
| Dynamic modeling and attitude control of flexible solar sail spacecraft for deep space exploration |
| 摘要点击 2073 全文点击 712 投稿时间：2019-06-30 修订日期：2020-02-27 |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| DOI编号 10.7641/CTA.2019.90503 |
| 2019,36(12):2019-2027 |
| 中文关键词 太阳帆航天器 动力学建模 姿态控制 柔性 仿真 |
| 英文关键词 Solar sail spacecraft dynamic modeling control flexible simulation |
| 基金项目 国家自然科学基金项目(61690215, 61640304, 61573060, 61203093，61803027), 国家杰出青年科学基金(61525301) |
|
| 中文摘要 |
| 柔性太阳帆完整的仿真模型包括多体动力学、刚柔耦合、以及太阳辐射光压模型，导致控制设计十分复杂。针对带有控制杆的太阳帆，本文采用拉格朗日方程和有限元方法，给出了解析形式的面向控制的模型。所推导的刚柔耦合动力学模型便于理解双框架控制杆的短周期运动，姿态与柔性太阳帆的耦合特性，以及在太阳光压恢复力矩下的静稳定姿态长周期运动。基于带控制杆的太阳帆的多时间尺度特性，给出了双回路控制结构，用于实现航天器俯仰轴和偏航轴的姿态控制。内回路设计为比例-微分（PD）控制器，用于实现质心位置的调整。外回路设计为比例-积分-微分（PID）控制器，用于阻尼姿态运动，并保持在平衡太阳光压力矩下的期望姿态。因此，将控制问题分解为低阶子问题，实现了在不同频带上的设计。仿真结果验证了动力学和姿态控制设计方法的有效性。 |
| 英文摘要 |
| Full simulation models for flexible solar sail spacecraft include multi-body dynamics, complex interplay between
flexible and rigid modes, along with solar radiation pressure model, resulting in intractable systems for control design.
In this paper, for a solar sail spacecraft with a control boom, a control-oriented model in closed form is obtained
by Lagrange equation and finite element method. The deduced rigid-flexible coupling dynamic model allows a well
understanding of the short-term motion of a two-axis gimbaled control boom, the coupling properties between attitude
and flexible spars, and the long-term motion of statically stable attitude under solar-pressure restoring torque. Based on
the multi-time-scale property of the solar sail spacecraft with a control boom, a dual-loop control structure is proposed
to change the pitch axis and yaw axis attitude of the spacecraft, employing a gimbaled control boom. The inner-loop
is designed as a proportional-derivative (PD) controller to realize the regulation of the center of mass. The outer-loop
is designed as a proportional-integral-derivative (PID) controller to damping the oscillate motion and maintain the
desired attitude under balanced solar-pressure torque. As a result, the full control problem is decomposed into lowerorder
subproblems, which are solved at different frequency band. Simulation results are presented that validate the
dynamic modeling and attitude control design approach. |
|
|
|
|
|