Robustness Studies of Output Predictive Dead-Beat Control for Wing Flutter Application.
Abstract
A new discrete control law is implemented and examined. Robustness to noise and model errors of the control law as sample rate varies is analyzed. This analysis is conducted while controlling several different very lightly damped, single input/single output systems which are representative of the flutter dynamics of the B-52E wing. The control law performance is different at separate sample rates. A distinct range of sample rates. Another range is found to be more robust when there exists an error in the models used to calculate the closed loop control law. When these ranges of sample rates intersect, the robustness characteristics at those sample rates is found to be good with respect to both noise and model mismatch. As theoretically predicted in a relationship between condition number of the system Hankel matrix and robustness seems to exist. Hence, these simulated results appear to validate the theoretical results on robustness predicted by Reid, but on the other hand, these simulated results indicate that the total analysis of 'robustness' is a very complex issue and cannot, at this point, be totally predicted by such a parameter as simple as the condition number of the Hankel matrix. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1979
- Accession Number
- ADA085709
Entities
People
- Earl H. Kirkwood Jr
Organizations
- Air Force Institute of Technology