Modeling-Error-Driven Performance-Seeking Direct Adaptive ControlThis paper presents a stable discrete-time adaptive law that targets modeling errors in a direct adaptive control framework. The update law was developed in our previous work for the adaptive disturbance rejection application. The approach is based on the philosophy that without modeling errors, the original control design has been tuned to achieve the desired performance. The adaptive control should, therefore, work towards getting this performance even in the face of modeling uncertainties/errors. In this work, the baseline controller uses dynamic inversion with proportional-integral augmentation. Dynamic inversion is carried out using the assumed system model. On-line adaptation of this control law is achieved by providing a parameterized augmentation signal to the dynamic inversion block. The parameters of this augmentation signal are updated to achieve the nominal desired error dynamics. Contrary to the typical Lyapunov-based adaptive approaches that guarantee only stability, the current approach investigates conditions for stability as well as performance. A high-fidelity F-15 model is used to illustrate the overall approach.
Document ID
20090026382
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Kulkarni, Nilesh V. (NASA Ames Research Center Moffett Field, CA, United States)
Kaneshige, John (NASA Ames Research Center Moffett Field, CA, United States)
Krishnakumar, Kalmanje (NASA Ames Research Center Moffett Field, CA, United States)
Burken, John (NASA Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 24, 2013
Publication Date
August 18, 2008
Subject Category
Aircraft Stability And Control
Report/Patent Number
ARC-E-DAA-TN-171Report Number: ARC-E-DAA-TN-171
Meeting Information
Meeting: AlAA Guidance Navigation and Control Conference
Location: Hawaii
Country: United States
Start Date: August 18, 2008
Sponsors: American Inst. of Aeronautics and Astronautics