You are here

Characterizing the Impact of Control Surfaces Free-Play on Flutter

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-10-C-0447
Agency Tracking Number: N10A-003-0664
Amount: $70,000.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: N10A-T003
Solicitation Number: 2010.A
Solicitation Year: 2010
Award Year: 2010
Award Start Date (Proposal Award Date): 2010-07-30
Award End Date (Contract End Date): 2011-02-28
Small Business Information
MONROE, CT 06468
United States
DUNS: 180516577
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Serkan Ozbay
 Manager, Aerospace Progs.
 (203) 874-3100
Business Contact
 Yogesh Mehrotra
Title: Vice President
Phone: (203) 874-3100
Research Institution
 Georgia Institute of Technology
 Dewey Hodges
270 Ferst Drive
Atlanta, GA 30332
United States

 (404) 894-8201
 Nonprofit College or University

Free-play nonlinearity of the control surfaces has a direct impact on aircraft’s dynamic stability characteristics. . It is impossible to design and manufacture a control surface with zero free-play. As control surface free-play increases, tighter limits must be imposed on the aircraft mission capability. Typically, researchers have utilized an oversimplified piecewise-linear torque-rotation relationship to assess the impact of control surface free-play on flutter. This simplistic approach fails to consider the effects of complex dynamic phenomena, such as intermittent contact and friction between surfaces, that occur as control surface moves from free-play region to non-free-play region and vice versa. Materials Technologies Corporation and Georgia Tech propose an advanced structural analysis tool for characterizing the impact of control surfaces free-play on flutter based on the nonlinear multibody dynamics analysis concept. In our approach, the complete hardware of the wing structure, including the mechanism that results in free-play, are modeled as individual dynamic elements; capturing the complex dynamic phenomena occurring at the transition region of free-play. Phase I concept feasibility of our multibody dynamics based approach will be demonstrated through comparisons between the numerical predictions and subsonic wind tunnel test results for horizontal tails. Proposed approach will be further refined and validated in Phase II with transonic and supersonic wind tunnel tests. Once developed, our innovative tool will provide a quick construction of the structural model, and accurate prediction of the stability behavior of control surfaces with free-play.

* Information listed above is at the time of submission. *

US Flag An Official Website of the United States Government