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Title: Nonlinear power flow feedback control for improved stability and performance of airfoil sections

Abstract

A computer-implemented 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 time-dependent response of the airfoil's pitch angle, .alpha.. The computer model calculates limit-cycles 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:  
AC04-94AL85000
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 computer-implemented 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 time-dependent response of the airfoil's pitch angle, .alpha.. The computer model calculates limit-cycles 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}
}

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