The first experimental ring laser gyroscope was demonstrated in the US by Macek and Davis in 1963. The technology has since been developed by a number of companies and establishments world-wide. 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. 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, meaning it can be used in aircraft. Unlike a mechanical gyroscope, the device does not resist changes to its orientation.
RLGs, while more accurate than mechanical gyroscopes, suffer from an effect known as "lock-in" at very slow rotation rates. When the ring laser is rotating very slowly, the frequencies of the counter-rotating lasers become very close (within the laser bandwidth). At this low rotation, the nulls in the standing wave tend to "get stuck" on the mirrors, locking the frequency of each beam to the same value, and the interference fringes no longer move relative to the detector; in this scenario, the device will not accurately track its angular position over time.
Dithering can compensate for lock-in. The entire apparatus is twisted and untwisted about its axis at a rate convenient to the mechanical resonance of the system, thus ensuring that the angular velocity of the system is usually far from the lock-in threshold. Typical rates are 400 Hz, with a peak dither velocity of 1 arc-second per second.
A related device is the fiber optic gyroscope which operates similarly to the ring gyro, but implementing transmission paths with a coiled fiber optic cable.
Primary applications include navigation systems on commercial airliners, ships and spacecraft, where RLGs are often referred to as an Inertial Reference System. In these applications, it has replaced its mechanical counterpart, the Inertial guidance system.
Researchers Submit Patent Application, "Mitigation of Block Bending in a Ring Laser Gyroscope Caused by Thermal Expansion or Compression of a Circuit Board", for Approval
Apr 24, 2013; By a News Reporter-Staff News Editor at Electronics Newsweekly -- From Washington, D.C., VerticalNews journalists report that a...
US Patent Issued to Honeywell International on March 15 for "Enhanced Scale Factor Ring Laser Gyroscope" (Minnesota Inventor)
Mar 17, 2011; ALEXANDRIA, Va., March 17 -- United States Patent no. 7,907,284, issued on March 15, was assigned to Honeywell International Inc....