Gyrocompassing mode of the strapdown inertial navigation system

A gyrocompassing mode of the strapdown inertial navigation systems (SINS) was presented. SINS has been composed of Inertial Measurement Unit (IMU) and navigation computer. IMU consists of triad accelerometers, gyroscopes and a circuit of signal processing. It is received a full expression for the error of gyrocompassing depending from errors of gyroscope, accelerometers and latitude source. It was estimated the errors of gyroscope and accelerometers on the assumption of the required the error of gyrocompassing. Also, it is shown that calibration results are effected to the error of gyrocompassing. It is brought the simulation results of impact any factors such as bias instability of gyroscopes, scale factor instability of gyroscopes, bias instability of accelerometers, scale factor instability of accelerometers, and misalignment of measurement frame axes onto the error of gyrocompassing mode. It is shown that maximum influence on to the error of gyrocompassing mode has got the bias instability of gyroscopes.