Calibration method for pointing angle of launch system
Aiming at the problem of low efficiency and being subject to weather which exists in tradi-tional star sighting methods,a model-based calibration method was proposed.In that method,the chassis was abstracted into a linear flat plate model,and its error was represented by three parameters of pitch,yaw and roll,and thus the pointing angle including the model error was obtained.Mean-while,a virtual space datum can be established by high-precision satellite navigation equipment.Using the equivalent relationship between the two,the error parameters were solved and corrected by the Newton iteration method.Theoretical and simulation analysis shows that the entire model can be cal-culated with only 2 measurement points,which improves the calibration efficiency,that the influence of the measurement accuracy of the datum can be ignored as long as the reference point is more than 1 km away from the barrel,and that by reasonable selection of the reference point,the calibration residual of the pointing angle can be controlled within 0.001 rad.
NETL
NSTL
万方数据
