| 引用本文: | 屈耀红,余自权,张友民.无人机空中加油过程中分数阶滑模会合导引控制[J].控制理论与应用,2015,32(11):1464~1469.[点击复制] |
| QU Yao-hong,YU Zi-quan,ZHANG Youmin.Fractional-order sliding-mode guidance control for rendezvous of unmanned aerial vehicles during air refueling[J].Control Theory and Technology,2015,32(11):1464~1469.[点击复制] |
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| 无人机空中加油过程中分数阶滑模会合导引控制 |
| Fractional-order sliding-mode guidance control for rendezvous of unmanned aerial vehicles during air refueling |
| 摘要点击 2147 全文点击 1373 投稿时间：2015-05-30 修订日期：2015-11-21 |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| DOI编号 10.7641/CTA.2015.50477 |
| 2015,32(11):1464-1469 |
| 中文关键词 无人机 空中加油 自主会合 末端约束 分数阶滑模变结构控制 |
| 英文关键词 UAV air refueling automatic rendezvous terminal constraint fractional-order sliding-mode control |
| 基金项目 国家自然科学基金项目(61473229, 60974146)资助 |
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| 中文摘要 |
| 针对带末端角度和末端速度约束的无人机空中加油自主会合问题, 设计了一种3维分数阶滑模导引律, 使
无人机在无加油机主动配合的情况下具备自主会合能力. 首先, 根据无人机与加油机之间的相对运动关系, 设计
了3维比例导引规律, 使无人机能够到达期望的加油位置. 其次, 利用滑模控制的强鲁棒性特点以及分数阶微积分的
精细控制特性, 基于变结构理论和李雅普诺夫稳定性理论设计了一种带有末端角度约束的3维分数阶滑模变结构控
制律, 并用所设计的分数阶滑模控制律对3维比例导引指令进行重构, 使无人机能以期望的末端追踪角度到达加油
位置. 然后, 构造了速度指令生成器, 对无人机的末端速度进行约束. 最后, 对所设计的导引律进行了仿真验证,仿真
结果表明所设计出来的导引律能满足追踪角度和速度约束的要求. |
| 英文摘要 |
| A guidance law based on fractional-order sliding-mode control is developed to deal with the terminal angle
and velocity constraints of unmanned aerial vehicle (UAV) in automatic rendezvous during air refueling. This law makes
the UAV possess the ability to rendezvous with the tanker aircraft without active cooperation from the tanker aircraft.
By considering the relative motion in three-dimensional space between the UAV and the tanker aircraft, we adopt the
proportional navigation guidance (PNG) law in three-dimensional space to make the UAV fly to the desired formation point
for refueling. Then, by making use of the robustness of the sliding-mode control and the meticulous characteristics of the
fractional calculus, we develop a sliding-mode control law with fractional order to restrict the chasing angles of the UAV
based on the variable structure control theory and the Lyapunov stability theory. The obtained sliding-mode control law
with fractional order is employed to modify the PNG law, the resultant law will make the UAV possess the ability to fly to
the desired formation point with the desired terminal chasing angle. Finally, a velocity command generator is developed to
constrain the terminal velocity of the UAV. Simulations are carried out to validate the proposed guidance law; the results
show that the designed guidance law achieves good control performance and satisfies the terminal angle constraint and the
terminal velocity constraint. |
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