GPS Integrity Monitoring with an Aerodynamic Model and Low Quality INS
Bruggemann, Troy S., Greer, Duncan G., & Walker, Rodney A. (2007) GPS Integrity Monitoring with an Aerodynamic Model and Low Quality INS. In International Global Navigation Satellite Systems Society IGNSS Symposium 2007, 4-6 December, Sydney, Australia.
For civilian general aviation, the Ground-based Regional Augmentation System (GRAS) is a cost-effective system (compared to Space-Based Augmentation Systems) which is able to provide a high degree of GPS accuracy and integrity to meet aviation requirements for all modes of flight down to Approach with Vertical Guidance (APV). However, since GRAS corrections are transmitted to aircraft from ground-based VHF broadcast stations, the GRAS signal-in-space may not always be received. The signal may be masked by surrounding terrain when an aircraft is on approach, or there may be gaps in the network coverage. During a GRAS outage an alternative integrity monitoring system is required to allow continuous navigation. Another requirement is that a backup integrity monitoring system must be as low cost as possible. Building upon work presented in Greer et al. (2006), a new method is investigated which involves using a combination of GPS, low performance (low-cost) Micro-Electro-Mechanical Systems (MEMS) Inertial Navigation Sensors (INS), and an aerodynamic model of the aircraft. This information is combined in an Extended Kalman Filter (EKF). The novel aspect of this architecture is the inclusion of an aerodynamic model for the GPS integrity monitoring. During a GRAS outage, the aerodynamic model brings a greater level of robustness to the integrity monitoring procedure than the low quality inertial sensors can provide alone. This method is also highly autonomous because all measurements are local to the aircraft, without requiring external aids. By computer simulation it is shown that the aerodynamic model may replace the MEMS INS as a source of dynamic information in the EKF. This allows the benefits of using an EKF and filtered fault detection algorithm to be obtained. It is shown that a more stable and lower HPL is achieved under changing satellite conditions than a GPS-only RAIM algorithm.
Impact and interest:
Citation countsare sourced monthly fromand citation databases.
These databases contain citations from different subsets of available publications and different time periods and thus the citation count from each is usually different. Some works are not in either database and no count is displayed. Scopus includes citations from articles published in 1996 onwards, and Web of Science® generally from 1980 onwards.
Citations counts from theindexing service can be viewed at the linked Google Scholar™ search.
Full-text downloadsdisplays the total number of times this work’s files (e.g., a PDF) have been downloaded from QUT ePrints as well as the number of downloads in the previous 365 days. The count includes downloads for all files if a work has more than one.
|Item Type:||Conference Paper|
|Additional Information:||For more information, please refer to the conference website (see hypertext link) or contact the authors.|
|Subjects:||Australian and New Zealand Standard Research Classification > ENGINEERING (090000) > AEROSPACE ENGINEERING (090100)|
|Divisions:||Current > Research Centres > Australian Research Centre for Aerospace Automation|
Past > QUT Faculties & Divisions > Faculty of Built Environment and Engineering
|Copyright Owner:||Copyright 2007 (please consult authors)|
|Deposited On:||11 Dec 2007|
|Last Modified:||29 Feb 2012 23:38|
Repository Staff Only: item control page