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INS/GPS Integration Architectures
MASSACHUSETTS INST OF TECH LEXINGTON MA
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An inertial navigation system INS exhibits relatively low noise from second to second, but tends to drift over time. Typical aircraft inertial navigation errors grow at rates between 1 and 10 nmih 1.8 to 18 kmh of operation. In contrast, Global Positioning System GPS errors are relatively noisy from second to second, but exhibit no long-term drift. Using both of these systems is superior to using either alone. Integrating the information from each sensor results in a navigation system that operates like a drift-free INS. There are further benefits to be gained depending on the level at which the information is combined. This presentation will focus on integration architectures, including loosely coupled, tightly coupled, and deeply integrated configurations. Deep integration is trademarked by Draper Laboratory. The advantages and disadvantages of each level of integration will be listed. Examples of current and future systems will be cited.
APPROVED FOR PUBLIC RELEASE