| Popis: |
Integrated omega/inertial navigation systems appear attractive in airborne applications since the excellent short-term accuracy of an inertial navigator is well-complemented by the intermittent availability of bounded, moderately accurate OMEGA position fixes. There are a number of different approaches which can be taken to accomplish the desired system integration; three such approaches are considered. The first involves a straightforward output reset, the second is essentially a Kalman-based variant of rate-aiding and the third involves conventional optimal integration. These schemes are evaluated using models for various navigation system errors to yield predictions of system position and velocity error behavior. Additionally, the schemes are compared on the basis of operational factors such as ease of implementation and computer utilization. |
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