Separation Of Guidance Instrumentation Error For Glide Missile Based On Observability

The separation of guidance instrumentation error is nothing but important to the hit accuracy of the glide missile which is one of the development directions of the missile weapon.Taking the glide missile as the study subject,this paper aims at finding new ways to separate guidance instrumentation error so that the separation accuracy can be improved.The major work and conclusions can be concluded as follows:The guidance instrumentation separation model of glide missile is established.Pointing at the inertial sensor used in the navigation system of glide missile,the error models are established for the gyros and the accelerometers respectively.Based on the error models and the relationship between the instrumentation error and the difference of the telemetry data and the exterior data,the separation model of guidance instrumentation error is derived and established.The calculating process of the circumstance function matrix and the difference between the telemetry data and exterior data is briefly introduced.And the valid of the separation model is examined and certified by simulation.The observability of the instrumentation error coefficients is studied.According to the output sensitivity theory and countering the guidance instrumentation error,the sensitivity model is constructed.The observability of each error coefficient is analyzed quantitatively.The sensitivity curve diagram of every error coefficient is yielded via the simulation data during flight.The principle to pick out error coefficients is drafted and the separation model is reconstructed.Using the least square method,the guidance instrumentation errors are separated noise-freely for the original model and the reconstructed model.The relative errors of the separation results are compared.Furthermore,the superiority of the reconstructed model is illustrated.A brand new separation algorithm is proposed.The fundamental of the new algorithm is briefly introduced.The de-noising is carried out based on wavelet and the separation is actualized based on the recursive extended least square method.Adding white noise with different standard deviation to the powered phase simulation data,the proposed algorithm is tested.It can be concluded from the separation results and the relative errors that the new algorithm has a strong robustness to noise and that although the standard deviation of the added noise is much bigger than the present level,the separation results are quite close to the true value of error coefficients.Also,it is found that the accuracy of the separation results of the new algorithm can be well-matched to the results of least square method without any noise.The fitting effect of difference between the telemetry data and exterior data is conveyed by the comparison of the velocity residual error.The instrumentation error separation is carried out based on the simulation data of gliding phase.Focusing on the long period of gliding,the separation of guidance instrumentation error is carried out.Comparing the separation results of glide phase with the results of passive phase,the characteristic of the gliding phase separation is analyzed and interpreted.A novel idea is provided to separate the guidance instrumentation error and its feasibility is verified.