A High Performance Airborne INS/GPS Integrated Navigation System,
Abstract
The system architecture and the trade-offs that drive its evolution are examined for a practical high-performance Integrated Navigation System designed for a number of current requirements. The system incorporates a 4 gimbal inertial navigator of inherently high stand-alone performance, integrated with a state-of-the-art 5 channel P-code GPS receiver. The system partitioning and interfacing are configured to optimise system accuracy during potentially lengthy periods when a full GPS solution may be unavailable, while providing satisfactory integrity under reversionary conditions. The main Kalman Filter takes pseudo-range and range rate measurements from the GPS rather than position and velocity and in primary navigation mode models INS and GPS error parameters. The Kalman Filter in the GPS receiver operates independently to provide the desired reversionary capability. The system architecture both in hardware and software, allows a high degree of inherent flexibility which is required to tailor the Integrated Navigation System to a wide variety of specific applications.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 04, 1989
- Accession Number
- ADP005819
Entities
People
- David I. Callender