Nonlinear power flow feedback control for improved stability and performance of airfoil sections
Abstract
A computerimplemented method of determining the pitch stability of an airfoil system, comprising using a computer to numerically integrate a differential equation of motion that includes terms describing PID controller action. In one model, the differential equation characterizes the timedependent response of the airfoil's pitch angle, .alpha.. The computer model calculates limitcycles of the model, which represent the stability boundaries of the airfoil system. Once the stability boundary is known, feedback control can be implemented, by using, for example, a PID controller to control a feedback actuator. The method allows the PID controller gain constants, K.sub.I, K.sub.p, and K.sub.d, to be optimized. This permits operation closer to the stability boundaries, while preventing the physical apparatus from unintentionally crossing the stability boundaries. Operating closer to the stability boundaries permits greater power efficiencies to be extracted from the airfoil system.
 Inventors:
 Issue Date:
 Research Org.:
 Sandia National Laboratories (SNL), Albuquerque, NM, and Livermore, CA (United States)
 Sponsoring Org.:
 USDOE
 OSTI Identifier:
 1092897
 Patent Number(s):
 8527247
 Application Number:
 12/633,045
 Assignee:
 Sandia Corporation (Albuquerque, NM)
 Patent Classifications (CPCs):

G  PHYSICS G05  CONTROLLING G05B  CONTROL OR REGULATING SYSTEMS IN GENERAL
 DOE Contract Number:
 AC0494AL85000
 Resource Type:
 Patent
 Country of Publication:
 United States
 Language:
 English
 Subject:
 97 MATHEMATICS AND COMPUTING
Citation Formats
Wilson, David G., and Robinett, III, Rush D. Nonlinear power flow feedback control for improved stability and performance of airfoil sections. United States: N. p., 2013.
Web.
Wilson, David G., & Robinett, III, Rush D. Nonlinear power flow feedback control for improved stability and performance of airfoil sections. United States.
Wilson, David G., and Robinett, III, Rush D. Tue .
"Nonlinear power flow feedback control for improved stability and performance of airfoil sections". United States. https://www.osti.gov/servlets/purl/1092897.
@article{osti_1092897,
title = {Nonlinear power flow feedback control for improved stability and performance of airfoil sections},
author = {Wilson, David G. and Robinett, III, Rush D.},
abstractNote = {A computerimplemented method of determining the pitch stability of an airfoil system, comprising using a computer to numerically integrate a differential equation of motion that includes terms describing PID controller action. In one model, the differential equation characterizes the timedependent response of the airfoil's pitch angle, .alpha.. The computer model calculates limitcycles of the model, which represent the stability boundaries of the airfoil system. Once the stability boundary is known, feedback control can be implemented, by using, for example, a PID controller to control a feedback actuator. The method allows the PID controller gain constants, K.sub.I, K.sub.p, and K.sub.d, to be optimized. This permits operation closer to the stability boundaries, while preventing the physical apparatus from unintentionally crossing the stability boundaries. Operating closer to the stability boundaries permits greater power efficiencies to be extracted from the airfoil system.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2013},
month = {9}
}