GPS INS Integration Application in Flight Management System
Flight management system (FMS) is a specialized
computer system that automates a wide variety of in-flight tasks,
reducing the workload on the flight crew to the point that modern
aircraft no longer carry flight engineers or navigators. The primary
function of FMS is to perform the in-flight management of the flight
plan using various sensors (such as GPS and INS often backed up by
radio navigation) to determine the aircraft's position. From the
cockpit FMS is normally controlled through a Control Display Unit
(CDU) which incorporates a small screen and keyboard or touch
screen. This paper investigates the performance of GPS/ INS
integration techniques in which the data fusion process is done using
Kalman filtering. This will include the importance of sensors
calibration as well as the alignment of the strap down inertial
navigation system. The limitations of the inertial navigation systems
are investigated in order to understand why INS sometimes is
integrated with other navigation aids and not just operating in standalone
mode. Finally, both the loosely coupled and tightly coupled
configurations are analyzed for several types of situations and
operational conditions.
[1] Mohander, S.G., Lawrance, R.W., Angus, P.A. Global positioning
system inertial navigation system and integration, JohnWiley & Sons,
2001.
[2] Titterton D.H. and Weston, J.L. (1997): "Strapdown inertial navigation
technology;" Peter Peregrinus Ltd., London, UK, 1997.
[3] El-Sheimy." Inertial techniques and INS/DGPS Integration". ENGO
623- Lecture Notes, the University of Calgary, Department of Geomatics
Engineering, Calgary (2004).
[4] Hoffmann-Wellenhof, B., H. Lichtenegger, and J. Collins "Global
positioning System; Theory and Practice", Springer New York. (2001).
[5] El-Rabbany, A., "Introduction to GPS: the global positioning system".
(Artech House mobile communications series). ┬® 2002 ARTECH
HOUSE, INC. 685 Canton Street Norwood, MA 02062.
[6] B. L. Stevens and F. L. Lewis. Aircraft Control and Simulation. John
Wiley & Sons, Inc., 1992.
[7] Greg Welch, "An Introduction to the Kalman Filter" Gary Bishop
University of North Carolina at Chapel Hill Department of Computer
Science Chapel Hill, NC 27599-3175 (2001).
[1] Mohander, S.G., Lawrance, R.W., Angus, P.A. Global positioning
system inertial navigation system and integration, JohnWiley & Sons,
2001.
[2] Titterton D.H. and Weston, J.L. (1997): "Strapdown inertial navigation
technology;" Peter Peregrinus Ltd., London, UK, 1997.
[3] El-Sheimy." Inertial techniques and INS/DGPS Integration". ENGO
623- Lecture Notes, the University of Calgary, Department of Geomatics
Engineering, Calgary (2004).
[4] Hoffmann-Wellenhof, B., H. Lichtenegger, and J. Collins "Global
positioning System; Theory and Practice", Springer New York. (2001).
[5] El-Rabbany, A., "Introduction to GPS: the global positioning system".
(Artech House mobile communications series). ┬® 2002 ARTECH
HOUSE, INC. 685 Canton Street Norwood, MA 02062.
[6] B. L. Stevens and F. L. Lewis. Aircraft Control and Simulation. John
Wiley & Sons, Inc., 1992.
[7] Greg Welch, "An Introduction to the Kalman Filter" Gary Bishop
University of North Carolina at Chapel Hill Department of Computer
Science Chapel Hill, NC 27599-3175 (2001).
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:52960", author = "Othman Maklouf and Abdurazag Ghila and Saleh Gashoot and Ahmed Abdulla", title = "GPS INS Integration Application in Flight Management System", abstract = "Flight management system (FMS) is a specialized
computer system that automates a wide variety of in-flight tasks,
reducing the workload on the flight crew to the point that modern
aircraft no longer carry flight engineers or navigators. The primary
function of FMS is to perform the in-flight management of the flight
plan using various sensors (such as GPS and INS often backed up by
radio navigation) to determine the aircraft's position. From the
cockpit FMS is normally controlled through a Control Display Unit
(CDU) which incorporates a small screen and keyboard or touch
screen. This paper investigates the performance of GPS/ INS
integration techniques in which the data fusion process is done using
Kalman filtering. This will include the importance of sensors
calibration as well as the alignment of the strap down inertial
navigation system. The limitations of the inertial navigation systems
are investigated in order to understand why INS sometimes is
integrated with other navigation aids and not just operating in standalone
mode. Finally, both the loosely coupled and tightly coupled
configurations are analyzed for several types of situations and
operational conditions.", keywords = "GPS, INS, Kalman Filter.", volume = "6", number = "11", pages = "2355-11", }