A control system for experimental platform of micro aerial vehicle based on C8051F020
|更新时间:2020-08-12
|
A control system for experimental platform of micro aerial vehicle based on C8051F020
Optics and Precision EngineeringVol. 15, Issue 5, Pages: 713-718(2007)
作者机构:
上海大学 精密机械工程系 上海,200072
作者简介:
基金信息:
DOI:
CLC:V27;TP273
Received:27 October 2006,
Revised:19 February 2007,
Published Online:30 May 2007,
Published:30 May 2007
稿件说明:
移动端阅览
LUO Jun, XING Lan-xing, ZHOU Yan, et al. A control system for experimental platform of micro aerial vehicle based on C8051F020[J]. Optics and precision engineering, 2007, 15(5): 713-718.
DOI:
LUO Jun, XING Lan-xing, ZHOU Yan, et al. A control system for experimental platform of micro aerial vehicle based on C8051F020[J]. Optics and precision engineering, 2007, 15(5): 713-718.DOI:
A control system for experimental platform of micro aerial vehicle based on C8051F020
A new measuring way different from the traditional deducting method for the angle of blade pitch was proposed based on high-speed camera and image processing. According to the experiment requirement
an experimental platform mainly based on the device of Micro Aerial Vehicle(MAV) and a new control system found on C8051F020 SCM were designed. In the platform
C8051F020 SCM was the MCU; the phase information of the propeller's main-shaft was tested with the micro position sensor and the PCA capture function of C8051F020 SCM. The four phase information of a propeller's main-shaft was gained by collecting the output signal of a position sensor; the motor speed was controlled by the output signal of PWM generated by C8051F020 SCM for controlling the motor speed up; a high-speed camera was touched off by the interrupt signal from the PCA capture in order to realize the synchronization between the speeding up of the motor and the taking pictures of the camera. This control system has compacted configuration and high reliability. Finally
using this system to control the MAV for simulating the forward flying
the electronic collector curve of MAV was obtained. It is proved that the proposed method and the experiment platform based this method can be used to measure the blade pitch and have met the design requirement completely.