For some years, the air traffic increase leads to minimize aircraft separation while improving safety. As a consequence, it's necessary to know precisely aircraft position with on-board performance monitoring and alerting (integrity), according to RNP principle (Requested Navigation Performance). The GNSS/INS (hybrid Inertial Navigation System) already provides high performance navigation solution, but the integrity requirement asks for new architectures and algorithms. The paper presents the architecture and main principles used in GNSS/INS to satisfy integrity navigation needs, i.e. Minimum operational performance requirements for integrity Hybrid function defined into DO-229 Annex R. The patented solution proposed by SAGEM is based on: (1) Tightly INS/GPS coupling, (2) Kalman filter Bank, (3) Calculation of localization protection radius associated with a 10-7/fh (Flight hour) probability of failure, (4) Detection and exclusion of faulty GPS measurement. The presentation will provide example of simulation and analysis done to assess performance (potential detected failure, time to alert, number of simulated flight hours).
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