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| Content Provider | IEEE Xplore Digital Library |
|---|---|
| Author | Ruba, C. Krishnan, P.S. Shanmugam, J. Lakshmi, S. |
| Copyright Year | 2005 |
| Description | Author affiliation: Dept. of Electron. Eng., MIT - Anna Univ., Tamil Nadu, India (Ruba, C.; Krishnan, P.S.; Shanmugam, J.; Lakshmi, S.) |
| Abstract | Vertical gyroscope is used to measure the pitch and roll attitude of the aircraft with respect to local vertical. Since it provides the state feedback for the basic stabilization loop, the error in the vertical gyro may destabilize the flight control system. The erection mechanism of a vertical gyro is based on mercury level bubble/electrolytic level sensors. The spin reference axis is driven to vertical by erection servo loop. But, during forward acceleration and horizontal acceleration, spin reference axis is driven to false vertical. Such vertical gyroscopes are used for controlling the roll, which helps to make the turns tighter. But it leads to wrong pitch indication, which affects the altitude holding capability of the aircraft. During high 'g' maneuvers (2g and beyond) even small tilts can make the turn to be more oscillatory ie., normal acceleration to be oscillating a lot. Normal acceleration, also known as load factor, is a nonlinear function of roll angle. To take care of these higher oscillations, control law has been designed. |
| File Size | 423869 |
| File Format | |
| ISBN | 0780393074 |
| DOI | 10.1109/DASC.2005.1563394 |
| Language | English |
| Publisher | Institute of Electrical and Electronics Engineers, Inc. (IEEE) |
| Publisher Date | 2005-10-30 |
| Publisher Place | USA |
| Access Restriction | Subscribed |
| Rights Holder | Institute of Electrical and Electronics Engineers, Inc. (IEEE) |
| Subject Keyword | Unmanned aerial vehicles Acceleration Gyroscopes Aircraft Construction State feedback Error correction Aerospace control Level control Servomechanisms |
| Content Type | Text |
| Resource Type | Article |
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