PDE Boundary Control for Flexible Articulated Aircraft Wings
Abstract
The paper considers a boundary control formulation for PDEs with a system output given by a spatial integral of weighted functions of the state. This formulation is directly applicable to the control of an aircraft with articulated exible wings, in which case the output of interest is a net aerodynamic force or moment. Flexible wings can be controlled via actuation at the root or the tip. The problem of beam twist is analysed in detail to illustrate the formulation, and it shown that the control law ensures that the error between the desired output signal and the actual output signal decreases exponentially to an uniform ultimate bound. Stability of the closed loop system is proved by Lyapunov techniques. The formulation is demonstrated by simulations.
Additional Information
© 2011 by Aditya A. Paranjape, Soon-Jo Chung and Miroslav Krstic. Published by the American Institute of Aeronautics and Astronautics, Inc. This project was supported in part by the Air Force Office of Scientific Research (AFOSR) under the Young Investigator Award Program (Grant No. FA95500910089) and the U.S. Army Research Office (ARO) under Award No W911NF-10-1-0296. The original problem of articulated wing aircraft was posed by Dr. Gregg Abate (AFRL).Attached Files
Published - PDEcontrol.pdf
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Additional details
- Eprint ID
- 73160
- Resolver ID
- CaltechAUTHORS:20161222-122638313
- FA95500910089
- Air Force Office of Scientific Research (AFOSR)
- W911NF-10-1-0296
- Army Research Office (ARO)
- Created
-
2016-12-23Created from EPrint's datestamp field
- Updated
-
2021-11-11Created from EPrint's last_modified field
- Caltech groups
- GALCIT
- Other Numbering System Name
- AIAA Paper
- Other Numbering System Identifier
- 2011-6486