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Adaptive Integrated Guidance and Control Design for Automatic Landing of a Fixed Wing Unmanned Aerial Vehicle.
- Source :
- Journal of Aerospace Engineering; Oct2012, Vol. 25 Issue 4, p490-500, 11p, 11 Diagrams, 6 Graphs
- Publication Year :
- 2012
-
Abstract
- This paper presents an automatic landing control design using adaptive, integrated guidance and control (IGC) logic. The proposed IGC design uses a combination of an adaptive output feedback inversion and backstepping techniques. The problem is formulated as an adaptive output feedback control problem for a line-of-sight-based chasing flight configuration. The design objective is to regulate the relative distance between the aircraft and the moving reference point on a landing pattern and two bearing angles maintaining turn coordination. Adaptive neural networks are trained online with available measurements to compensate for inversion error as a result of unmodeled dynamics and modeling errors of the aircraft in the design process. In addition, a reference command trajectory for the automatic landing control is designed in a way that the aircraft follows the landing pattern regardless of its initial position. The automatic landing system using IGC logic is evaluated using a sophisticated six-degrees-of-freedom nonlinear simulation program with the approach and landing scenario. [ABSTRACT FROM AUTHOR]
Details
- Language :
- English
- ISSN :
- 08931321
- Volume :
- 25
- Issue :
- 4
- Database :
- Complementary Index
- Journal :
- Journal of Aerospace Engineering
- Publication Type :
- Academic Journal
- Accession number :
- 82336450
- Full Text :
- https://doi.org/10.1061/(ASCE)AS.1943-5525.0000172