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Accession Number ADA581020
Title INS/GPS Integration Architectures.
Publication Date Mar 2010
Media Count 19p
Personal Author G. T. Schmidt R. E. Phillips
Abstract 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 nmi/h (1.8 to 18 km/h) 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.
Keywords Coupling(Interaction)
Global positioning system
Gps denied environments
Inertial navigation
Integration architectures
Nato furnished
Navigation technology

Source Agency Non Paid ADAS
NTIS Subject Category 76D - Navigation Systems
85F - Global Navigation Systems
Corporate Author Massachusetts Inst. of Tech., Lexington.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1325
Contract Number N/A

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