IMU inertial measurement equipment to the strapdown inertial navigation system has two acceleration sensor with three speed sensor (gyroscope, accelerometer) to feel the weight of the plane relative to the vertical acceleration, speed sensor is used to sense the angle information of the aircraft, the first part a two A/D converter, A/D converter with modeled variable IMU each sensor, converted to digital information by CPU after the calculation of the final output plane, inclined angle and pitch angle of sideslip angle.
The inertial navigation system is based on the classical mechanics of Newton. Assuming that acceleration is measured, the speed and azimuth changes of the object can be calculated by the continuous mathematical integration of the acceleration to the time. Inertial navigation system is a system that uses gyroscopes and accelerometers on the carrier to measure the carrier’s azimuth. Through the measurement data of gyroscopes and accelerometers, the motion of the carrier in the inertial reference coordinate system can be determined.
INS is the value of angular velocity and acceleration obtained by IMU measurement. The result is calculated by computer, and the overall execution of the system is able to determine the motion of the moving vehicle in the inertial reference frame.
From the above, it is seen that INS is included in the IMU measurement unit.
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