The invention relates to an inertial measurement unit (IMU) for rotating carriers, which mainly designs a high-performance microminiature inertial instrument scheme (mainly composed of parts of three groups of orthogonal gyros formed by four MEMS gyros, three orthogonal quartz digital accelerometers, a structure body, a secondary power supply, a signal processing and communication interface, and the like), and designs the effective compensation of random drift errors of the MEMS gyros by UKF Kalman filtering. The scheme of the invention has the characteristics of wide measuring range, small size, high dynamics, and low weight, is suitable for real-time measurement of flight attitude of a high-speed rotating missile body during a flight process, suitable for position and speed measurement of long-range rocket projectiles, middle and short-range terminal guided ammunition, ground weapon attitude stabilization systems, aerial bomb flight control systems, and unmanned plane heading and attitude systems. The scheme of the invention is also applicable to nuclear submarine strapdown positioning combination, environment swing and inclination measuring systems, inertial motion recording systems of various vehicles and ships, and the like.