Fiber optic gyroscope, as the core component of inertial navigation system, can provide high-precision three-dimensional angular velocity, position and attitude information in the aerospace field, realizing functions such as tracking and measurement of rocket launch, spacecraft stabilization, attitude measurement and control. In the field of navigation, fiber optic gyroscopes have become an important component of ship navigation equipment, providing high-precision heading information and achieving functions such as automatic north finding and pointing, attitude control, etc.

Fiber optic gyroscope is mainly composed of fiber optic ring, light source, photodetector, and signal processing system. Its working principle is based on the Sagnac effect, which means that when a beam of light travels in a circular channel, if the circular channel itself has a rotational speed, the time required for the light to travel along the direction of rotation of the channel is longer than the time required to travel along the opposite direction of rotation of the channel. By measuring this time or phase difference, the rotational angular velocity of the gyroscope can be calculated.