Self-adaptive IRU correction loop design interfacing with the ta

Details Self-adaptive IRU correction loop design interfacing with the ta Self-adaptive IRU correction loop design interfacing with the ta

1986-12-08

1988-11-08

Chin, Gary

Boots, shoes, and leggings

364462, 36457101, 235412, 342 62, 244 32, G06F 1550

Patent

active

047837446

ABSTRACT:
A method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position. Discrepancy parameters are introduced to indicate misalignment between missile and launching platform (or ship) inertial frames where the missile onboard executive computer simultaneously processes the data provided from missile onboard sensors and target relevant data uplinked from the launching platform. The discrepancy parameters are employed to construct correction factors used to reduce the discrepancies. This updated missile configuration is then coupled with the target state estimator outputs to reconstruct smoothed line-of-sight (LOS) angles for terminal homing engagement.

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