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基于核相關(guān)濾波的無(wú)人機偏航角跟蹤控制系統設計
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成都理工大學(xué)工程技術(shù)學(xué)院

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Design of uav yaw Angle tracking control System based on nuclear correlation filtering
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    摘要:

    針對非線(xiàn)性自抗擾控制技術(shù)設計的系統、線(xiàn)性自抗擾技術(shù)設計的系統受到噪聲影響,導致信號傳輸受到阻礙,出現偏航角跟蹤控制結果精準度低的問(wèn)題,提出了基于核相關(guān)濾波的無(wú)人機偏航角跟蹤控制系統設計。在系統總體架構支持下,采用STM32F407型號主控芯片,保證無(wú)人機控制系統穩定性。在方向盤(pán)下安裝有轉向角傳感器,為ESP電子控制單元提供方向盤(pán)。使用頻率為2.4 GHz遙控器接收機生成具有不同脈沖寬度PWM信號,通過(guò)控制旋翼偏航控制器,推動(dòng)旋翼在不同角度指令下旋轉。利用核相關(guān)濾波器過(guò)濾目標圖像,通過(guò)濾波器的輸運來(lái)估計目標運動(dòng)位置,并確定地面參考坐標系與無(wú)人機機體坐標系,構成無(wú)人機在空間中六個(gè)自由度,由此設計偏航角跟蹤控制軟件流程,跟蹤控制無(wú)人機偏航角。由實(shí)驗結果可知,該系統滾轉角與實(shí)際值軌跡一致,誤差為0;俯仰角與實(shí)際值軌跡有偏差,誤差為0.05°,為無(wú)人機向不同方向精準飛行提供系統支持。

    Abstract:

    Aiming at the problem that the system designed with nonlinear ADRC technology and the system designed with linear ADRC technology are affected by noise, which leads to the obstruction of signal transmission and the low accuracy of yaw Angle tracking control results, a design of uav yaw Angle tracking control system based on nuclear correlation filtering was proposed. Under the support of the overall system architecture, STM32F407 master control chip is adopted to ensure the stability of uav control system. Steering Angle sensors are mounted under the steering wheel to provide the steering wheel for the ESP electronic control unit. The 2.4ghz remote control receiver is used to generate PWM signals with different pulse width.By controlling the rotor yaw controller, the rotor is pushed to rotate under instructions from different angles. The target image is filtered by the nuclear correlation filter, the target motion position is estimated by the transport of the filter, and the ground reference coordinate system and the frame coordinate system of the UAV are determined, which constitute six degrees of freedom of the UAV in the space. Thus, the yaw Angle tracking and control software flow is designed to track and control the yaw Angle of the UAV. The experimental results show that the roll Angle of the system is consistent with the actual value trajectory, and the error is 0. There is a deviation between the pitch Angle and the actual value trajectory with an error of 0.05°, which provides system support for the uav to fly accurately in different directions.

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肖英楠.基于核相關(guān)濾波的無(wú)人機偏航角跟蹤控制系統設計計算機測量與控制[J].,2021,29(7):145-148.

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  • 收稿日期:2020-11-30
  • 最后修改日期:2020-12-21
  • 錄用日期:2020-12-21
  • 在線(xiàn)發(fā)布日期: 2021-07-23
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