A gradient descent algorithm with adjustable parameter for attitude estimation is developed,aiming at the attitude measurement for small unmanned aerial vehicle(UAV)in real-time flight conditions.The accelerometer and...A gradient descent algorithm with adjustable parameter for attitude estimation is developed,aiming at the attitude measurement for small unmanned aerial vehicle(UAV)in real-time flight conditions.The accelerometer and magnetometer are introduced to construct an error equation with the gyros,thus the drifting characteristics of gyroscope can be compensated by solving the error equation utilized by the gradient descent algorithm.Performance of the presented algorithm is evaluated using a self-proposed micro-electro-mechanical system(MEMS)based attitude heading reference system which is mounted on a tri-axis turntable.The on-ground,turntable and flight experiments indicate that the estimation attitude has a good accuracy.Also,the presented system is compared with an open-source flight control system which runs extended Kalman filter(EKF),and the results show that the attitude control system using the gradient descent method can estimate the attitudes for UAV effectively.展开更多
文章主要研究基于NI my RIO小型四旋翼飞行器的设计与实现,小型四旋翼飞行器拥有灵活小巧且软硬件结构比较简单的特点,并且以NI my RIO芯片为核心。飞行器的设计包括蓝牙通信模块,控制器模块,传感器检测模块,驱动模块、电源模块和电机...文章主要研究基于NI my RIO小型四旋翼飞行器的设计与实现,小型四旋翼飞行器拥有灵活小巧且软硬件结构比较简单的特点,并且以NI my RIO芯片为核心。飞行器的设计包括蓝牙通信模块,控制器模块,传感器检测模块,驱动模块、电源模块和电机执行模块。小型四旋翼飞行器采用的是PID控制算法。PID控制算法是自动控制系统的常用基本控制方式。通过PID控制算法调整,可以实现小型四旋翼飞行器的平稳飞行。展开更多
基金supported by the Fundamental Research Funds for the Central Universities(No.56XAA17075)
文摘A gradient descent algorithm with adjustable parameter for attitude estimation is developed,aiming at the attitude measurement for small unmanned aerial vehicle(UAV)in real-time flight conditions.The accelerometer and magnetometer are introduced to construct an error equation with the gyros,thus the drifting characteristics of gyroscope can be compensated by solving the error equation utilized by the gradient descent algorithm.Performance of the presented algorithm is evaluated using a self-proposed micro-electro-mechanical system(MEMS)based attitude heading reference system which is mounted on a tri-axis turntable.The on-ground,turntable and flight experiments indicate that the estimation attitude has a good accuracy.Also,the presented system is compared with an open-source flight control system which runs extended Kalman filter(EKF),and the results show that the attitude control system using the gradient descent method can estimate the attitudes for UAV effectively.
文摘文章主要研究基于NI my RIO小型四旋翼飞行器的设计与实现,小型四旋翼飞行器拥有灵活小巧且软硬件结构比较简单的特点,并且以NI my RIO芯片为核心。飞行器的设计包括蓝牙通信模块,控制器模块,传感器检测模块,驱动模块、电源模块和电机执行模块。小型四旋翼飞行器采用的是PID控制算法。PID控制算法是自动控制系统的常用基本控制方式。通过PID控制算法调整,可以实现小型四旋翼飞行器的平稳飞行。
