Abstract
Modern navigation systems represent an inherent part of avionic equipment onboard all aircraft categories. The standard navigation performance typically defined by accuracy, integrity, availability, and continuity is now complemented by the system’s ability to reduce CO2 emissions and fuel consumption. This article describes current navigation system development executed by Honeywell International for SAT (Small Aircraft Transportation) segment defined by CS-MMEL ATA 34 Navigation. The proposed solution is based on INS/GNSS hybridization extended by other aiding sensors available onboard the aircraft. To create a technological solution that meets the system operational requirements of the segment and at the same time comply with SWAP-C (Size, Weight, And Power Consumption Related to Cost) requirements is the aim of this research activity. The article describes proposed integration architecture based on hybridized core and other aiding sensors, such as radar altimeter and magnetometer. The assessment of previously mentioned aiding sensors was performed and impact on navigation performance was determined. The emphasis was mainly put on Inertial Measurement Unit (IMU) meeting the low-cost requirement for the overall architecture. The IMU error model definition and long-term thermal chamber measurements are the main tools for understanding the stochastic behaviour of the IMU’s. The accuracy improvement is further supported by implementing SBAS corrections in INS/GNSS hybridization. This is not a usual navigation solution for SAT segment, since, typically, standalone GNSS receiver with SBAS is used instead. The Monte Carlo simulations were performed to compare the performance of the proposed solution against system and operational requirements. A proprietary Honeywell tool for these large-scale simulations is capable to simulate the navigation exercise anywhere on the Earth using pre-defined trajectories with specific duration and simulated GNSS constellation to reflect the impact of the satellite geometry.
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