An on-launcher Calibration Method for Missile-borne Single-axis Rotation Strapdown Inertial Navigation System
Due to prolonged storage, the model parameters of the strapdown inertial navigation system undergo chan-ges compared to the laboratory calibration results, resulting in the system being unable to meet the navigation accuracy re-quirements. In order to meet the demand for the parameter stability of missile-borne strapdown inertial navigation systems and reduce the guarantee cost of regular calibration, an on-launcher calibration method for missile-borne single-axis rotation strapdown inertial navigation system is proposed. This method designs a calibration path by analyzing the excitation relation-ship between different maneuvering states and the parameters of inertial navigation to be calibrated. The state transformation extended Kalman filter( STEKF) is used to estimate state variables, and the influence of outer lever arm error is considered when calculating velocity observations. The simulation results show that this scheme can calibrate the bias and the scale fac-tor error of gyroscope and accelerometer within 10 min, the estimation accuracy of the STEKF model is better than that of the KF model in the presence of vibration noise interference. The relative errors of the state variables estimated by the STEKF model are all less than 15％, and the relative error of each parameter for the accelerometer is less than 8％. Field experiment verifies that this method can accurately calibrate the bias and the scale factor error of the strapdown inertial navi-gation system.
on-launcher calibrationstate transformation extended Kalman filter( STEKF)single-axis rotation strapdown inertial navigation systemobservabilityouter lever arm
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