四旋翼飞行器中升力波动的干扰与抑制

赵常均; 宫勋; 白越; 续志军; 徐东甫; 高庆嘉

doi:10.3788/OPE.20142209.2431

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四旋翼飞行器中升力波动的干扰与抑制

微纳技术与精密机械 | 更新时间：2020-08-13

- 四旋翼飞行器中升力波动的干扰与抑制
- Interference and inhibition of lift fluctuation on quadrotor aircraft
- 光学精密工程 2014年22卷第9期页码：2431-2437
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
  2. 中国科学院大学北京,中国,100049
- 作者简介：
- 基金信息：
  
  国家自然科学基金资助项目（No.11372309，No.61304017）();中国科学院知识创新工程重要方向性项目（No.yyyj-1112）()
- DOI：10.3788/OPE.20142209.2431
  中图分类号： V211.4
- 收稿日期：2013-11-28，
  
  修回日期：2014-01-05，
  
  纸质出版日期：2014-09-25
- 稿件说明：
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赵常均, 宫勋, 白越等. 四旋翼飞行器中升力波动的干扰与抑制[J]. 光学精密工程, 2014,22(9): 2431-2437

ZHAO Chang-jun, GONG Xun, BAI Yue etc. Interference and inhibition of lift fluctuation on quadrotor aircraft[J]. Editorial Office of Optics and Precision Engineering, 2014,22(9): 2431-2437
赵常均, 宫勋, 白越等. 四旋翼飞行器中升力波动的干扰与抑制[J]. 光学精密工程, 2014,22(9): 2431-2437 DOI： 10.3788/OPE.20142209.2431.

ZHAO Chang-jun, GONG Xun, BAI Yue etc. Interference and inhibition of lift fluctuation on quadrotor aircraft[J]. Editorial Office of Optics and Precision Engineering, 2014,22(9): 2431-2437 DOI： 10.3788/OPE.20142209.2431.

摘要

四旋翼飞行器旋翼产生的升力是在基值的基础上附加一系列频率特性和旋翼转速有关的高频分量。由于它会对飞行器的控制产生扰动，本文研究了这类高频升力分量对飞行器的影响并给出了抑制扰动的方法。首先，基于拉格朗日能量法建立四旋翼飞行器动力学模型；进而分析了高频升力分量与飞行器角速度扰动之间的关系。然后，将角速度反馈环节加入针对有色噪声的卡尔曼滤波器来抑制角速度扰动对控制器的影响。实验结果显示：与改进前相比，采用本文的方法对四旋翼原型机进行悬停控制可使控制量波动减少50%，高频控制量衰减至-17db以下。结果表明：采用本文的方法，可以有效地抑制升力波动对四旋翼飞行器的影响，提高飞行控制效率。

Abstract

The lift of a quad-rotor aircraft is composed of series frequencies related to the rotor speeds. As it will interferes the control of the aircraft

this paper analyzes the effect of high-frequency lift component on the aircraft and gives an inhibiting method for the lift fluctuation. Firstly

the dynamic model of quad rotor aircraft was established by Lagrangians method and the relational expression between the high-frequency lift component and the disturbance of aircraft angular velocity was obtained. According to the previous analysis

the angular velocity feedback loop was joined a Kalman filter for colored noise to restrain the disturbance of angular velocity acting on the controller. A prototype was designed. The testing results show when the proposed method is used in hovering control of the quad rotor aircraft

the control variable fluctuations decrease by 50% and the high frequency control volume attenuates to under -17 db as compared with that of traditional PID method

respectively. The method of this paper effectively solves the effect of lift fluctuation on the quad rotor aircraft and improves the efficiency of control.

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Keywords

references

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