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Sensors 2012, 12(7), 9823-9828; doi:10.3390/s120709823
Communication

A Micro-Machined Gyroscope for Rotating Aircraft

1,2,* , 2
 and 2
Received: 1 April 2012; in revised form: 23 May 2012 / Accepted: 1 June 2012 / Published: 23 July 2012
(This article belongs to the Special Issue Ultra-Small Sensor Systems and Components)
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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 silicon micromachining; gyroscope; rotating aircraft
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

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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.

AMA Style

Yan Q, Zhang F, Zhang W. A Micro-Machined Gyroscope for Rotating Aircraft. Sensors. 2012; 12(7):9823-9828.

Chicago/Turabian Style

Yan, Qingwen; Zhang, Fuxue; Zhang, Wei. 2012. "A Micro-Machined Gyroscope for Rotating Aircraft." Sensors 12, no. 7: 9823-9828.


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