We investigate strategies for guidance-level reconfiguration following changes in aircraft closed-loop dynamics. The guidance model for the vehicle under study is a maneuver automaton. We propose reconfiguration methods to handle changes in such vehicle dynamics using the Guidance Value Function that emerges from the solution to the underlying optimal trajectory generation problem. We illustrate our approach on a numerical example. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.
|Original language||English (US)|
|Title of host publication||AIAA Guidance, Navigation, and Control Conference and Exhibit|
|Publisher||American Institute of Aeronautics and Astronautics Inc.email@example.com|
|State||Published - Jan 1 2002|