Date of Award

Summer 2006

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Aerospace Engineering

Committee Director

Drew Landman

Committee Member

Colin P. Birtcher

Committee Member

Brett A. Newman

Call Number for Print

Special Collections; LD4331.E535 F38 2006

Abstract

Flight testing using a designed experiment was used to model pitch damping in the longitudinal short-period mode of an aircraft. Multi-step elevator maneuvers were flown at different angles of attack and power levels on an electrically powered, propeller-driven UltraStick 120 remotely controlled model A Central Composite Response Surface Design was used to select angle of attack and power levels for each maneuver. During post flight analysis it was discovered that power was not measured correctly for this purpose so advance ratio was selected as a replacement factor. Parameter estimation results for each maneuver were modeled globally using a single response surface. This experiment allowed global modeling of the pitch damping to be performed from just a few flight test maneuvers. Identified global models of pitch damping are plotted against angle of attack and power (or advance ratio) in a surface response plot, for nonlinear piloted simulations and for flight test data.

Rights

In Copyright. URI: http://rightsstatements.org/vocab/InC/1.0/ This Item is protected by copyright and/or related rights. You are free to use this Item in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you need to obtain permission from the rights-holder(s).

DOI

10.25777/wkb0-7622

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