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ring laser gyroscope
A ring laser gyroscope (RLG) consists of a ring laser having two counter-propagating modes over the same path in order to detect rotation. It operates on the principle of the Sagnac effect which shifts the nulls of the internal standing wave pattern in response to angular rotation. Interference between the counter-propagating beams, observed externally, reflects shifts in that standing wave pattern, and thus rotation.
==Description==
The first experimental ring laser gyroscope was demonstrated in the US by Macek and Davis in 1963.〔Warren M. Macek and D. T. M. Davis, Jr. (1963) "Rotation rate sensing with traveling-wave ring lasers," ''Applied Physics Letters'', vol. 2, pages 67–68.〕 Various organizations worldwide subsequently developed ring-laser technology further. Many tens of thousands of RLGs are operating in inertial navigation systems and have established high accuracy, with better than 0.01°/hour bias uncertainty, and mean time between failures in excess of 60,000 hours.
Ring laser gyroscopes can be used as the stable elements (for one degree of freedom each) in an inertial reference system. The advantage of using an RLG is that there are no moving parts (apart from the dither motor assembly, see further description below and laser-lock), compared to the conventional spinning gyroscope. This means there is no friction, which in turn means there will be no inherent drift terms. Additionally, the entire unit is compact, lightweight and virtually indestructible, making it suitable for use in aircraft. Unlike a mechanical gyroscope, the device does not resist changes to its orientation.
Contemporary applications of the Ring Laser Gyroscope (RLG) include an embedded GPS capability to further enhance accuracy of RLG Inertial Navigation Systems (INS)s on military aircraft, commercial airliners, ships and spacecraft. These hybrid INS/GPS units have replaced their mechanical counterparts in most applications. Where ultra accuracy is needed however, spin gyro based INSs are still in use today.〔Peter M. Taylor - INS Test Engineer Honeywell, Inc.〕
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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