Experimental and analytical techniques for extracting the aerodynamic damping-in-pitch parameter for orbital re-entry vehicles: An investigation of stability for space capsules
Issue Date
2007-05-31Author
Torgler, Bradley
Publisher
University of Kansas
Type
Thesis
Degree Level
M.S.
Discipline
Aerospace Engineering
Rights
This item is protected by copyright and unless otherwise specified the copyright of this thesis/dissertation is held by the author.
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Show full item recordAbstract
Aerodynamic damping is investigated in the subsonic, transonic and supersonic flight regimes for the Apollo and Expert orbital re-entry vehicles. Static moment and forced oscillation experiments are carried out on replica models in the von Karman Institute (VKI) S-1 Transonic-Supersonic wind tunnel. This is the first investigation to be done using the forced oscillation experimental technique in the VKI-S1. Oscillations are induced to match the reduced frequencies of flight vehicles based on their natural frequencies. A variety of mathematical models are developed to extract the aerodynamic damping-in-pitch parameter from the forced oscillation data. The results are compared to one another as well as to published data (where applicable). Free-to-tumble experimental data obtained for an Apollo model prior to this investigation is also evaluated using various mathematical models. Results show that classical analysis methods for extracting the aerodynamic damping-in-pitch parameter, which have been used many times prior to this investigation, continue to yield the most accurate measure for aerodynamic damping extraction. These include an outer-extremity envelope distribution method, which assumes a constant damping from one peak of pitch attitude to the next for free-to-tumble analysis and an energy conservation method based on hysteresis loops of pitching moment against pitch attitude for forced oscillation analysis.
Description
Thesis (M.S.)--University of Kansas, Aerospace Engineering, 2007.
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