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A Micro-Machined Gyroscope for Rotating Aircraft
School of Electronic Engineering, Beijing University of Posts and Telecommunications, Beijing 100876, China
Sensing Technique Research Center, Beijing Information Science and Technology University, Beijing 100101, China
* Author to whom correspondence should be addressed.
Received: 1 April 2012; in revised form: 23 May 2012 / Accepted: 1 June 2012 / Published: 23 July 2012
Abstract: In this paper we present recent work on the design, fabrication by silicon micromachining, and packaging of a new gyroscope for stabilizing the autopilot of rotating aircraft. It operates based on oscillation of the silicon pendulum between two torsion girders for detecting the Coriolis force. The oscillation of the pendulum is initiated by the rolling and deflecting motion of the rotating carrier. Therefore, the frequency and amplitude of the oscillation are proportional to the rolling frequency and deflecting angular rate of the rotating carrier, and are measured by the sensing electrodes. A modulated pulse with constant amplitude and unequal width is obtained by a linearizing process of the gyroscope output signal and used to control the deflection of the rotating aircraft. Experimental results show that the gyroscope has a resolution of 0.008 °/s and a bias of 56.18 °/h.
Keywords: silicon micromachining; gyroscope; rotating aircraft
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MDPI and ACS Style
Yan, Q.; Zhang, F.; Zhang, W. A Micro-Machined Gyroscope for Rotating Aircraft. Sensors 2012, 12, 9823-9828.
Yan Q, Zhang F, Zhang W. A Micro-Machined Gyroscope for Rotating Aircraft. Sensors. 2012; 12(7):9823-9828.
Yan, Qingwen; Zhang, Fuxue; Zhang, Wei. 2012. "A Micro-Machined Gyroscope for Rotating Aircraft." Sensors 12, no. 7: 9823-9828.