Study on Error Correction Model of Inertia and Star Compact Combination

摘要

According to the existing inertial and starlight integrated navigation affected by the horizontal reference error,an inertial and star compactly combined error correction model is studied.The state space model and the measurement model in the compact combination mode are derived through theoretical deduction.The new model taking into account the attitude error and position error of the inertial solution,the influence of the reference error of the inertial navigation system on the calculation result of the related parameters of the integrated navigation can be effectively suppressed,and the precision of the integrated navigation can be improved.In order to verify the correctness of the research theory,a set of simulation experiments was designed.The results show that under the set carrier simulation trajectory,the compact combination model studied has better error correction effect on speed,position and attitude parameters than the loose combination method.Parameters in the convergence rate,fluctuation range,and accuracy reflect better advantages.The navigation position accuracy under simulation conditions can reach within 300m.