Suboptimal Estimation of Inertial System Error States using Radar Area Correlation and Altimeter Position Measurements
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL GUIDANCE AND CONTROL DIRECTORATE
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The report describes one of several alternatives being explored to establish advanced guidance techniques for the Armys long range tactical missile, the PERSHING. The analysis is given for estimating the inertial measurement units error states in an aided terminal guidance mode. Position observations measured by a radar area correlation system and a radar altimeter are processed in an extended Kalman filter to yield the suboptimal estimates of the inertial measurement units errors. The dynamics of the inertial system are modeled in four coordinate systems to allow the choice of the least complex mechanization. To minimize on-board computer requirements, an analysis of the filters performance is made by comparing the optimal filter gains with a filter formulated with fixed gains chosen a posteriori from those computed optimally.
- Surface-Launched Guided Missiles
- Air Navigation and Guidance