High accuracy navigation and landing system using GPS/IMU system integration

摘要: In this paper, the accuracy, integrity and continuity of function requirements for automatic landing systems using satellite navigation are discussed. Such a system is integrated (INLS) developed by Deutsche Aerospace (DASA/Ulm, Germany). The concepts INLS presented. It shown how an INLS, based on integration (e.g., GPS) in realtime differential mode with inertial measurement unit (IMU) accuracy class attitude heading reference (AHRS), can meet requirements: results given mainly devoted to issues. Using Kalman filter techniques, in-flight calibration IMU performed. advantage integration, especially dynamic flight conditions during phases masking, explained. were proven means tests commuter aircraft laser tracker as reference. These have that short-term ( >