Sensitivity of the Steady-State Kalman Filters to Stability Derivatives Variations in an Inertial Navigation System

摘要

In a tactical missile with mid-course guidance, an Inertial Navigation System (INS) is required. Strapdown INS using Steady-State Kalman Filters (SKF) as estimators has been suggested and this kind of INS is considered to be easier and cheaper to implement than the gimbaled INS. This thesis investigates one aspect of the INS problem: The sensitivity of the SKF to inaccuracies in the filter parameters such as the stability derivatives. The analysis has been performed by varying each of the flight parameters over a given range and noting the effect on the accuracy of the filter. The great advantage of the analysis in the sensitivity of rms estimate errors to inaccuracies in the stability derivatives is that it points out clearly which derivatives are worthy of detailed accurate determination and which are not. (Author)