Pitching Model with Control Surface in Hypersonic Flow: Short Duration Ground Tests and Simulations
Paper
Paper/Presentation Title | Pitching Model with Control Surface in Hypersonic Flow: Short Duration Ground Tests and Simulations |
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Presentation Type | Paper |
Authors | Stern Nathan and Buttsworth David R. |
Journal or Proceedings Title | Proceedings of the 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2020) |
Year | 2020 |
Place of Publication | Canada |
ISBN | 9781624106002 |
Digital Object Identifier (DOI) | https://doi.org/0.2514/6.2020-2452 |
Web Address (URL) of Paper | https://arc.aiaa.org/doi/epdf/10.2514/6.2020-2452 |
Web Address (URL) of Conference Proceedings | https://arc.aiaa.org/doi/book/10.2514/MHYP20 |
Conference/Event | 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2020) |
Event Details | 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2020) Parent AIAA International Space Planes and Hypersonic Systems and Technologies Conference Delivery In person Event Date 10 to end of 12 Mar 2020 Event Location Montreal, Quebec, Canada |
Abstract | Experiments on a flat-plate model with a rear control surface were performed in a Mach 6 hypersonic wind tunnel with a flow duration of approximately 200 ms. Oscillations in pitch were initiated with the rapid onset of the flow, and the control surface was actuated to modulate the oscillations during the flow time of the hypersonic wind tunnel. Steady state CFD simulations were performed for the configuration with different control surface deflections to establish reference values for static pressures and aerodynamic forces acting on the model. A mathematical model which accommodated the motor performance and the backlash in the gearbox driving the control surface was also established. Using the aerodynamic force simulations from the CFD, the kinematic properties of the physical model, and a mathematical model for the control surface actuation, the dynamics of the physical model during the hypersonic flow was simulated and demonstrated good agreement with the experimental measurements. |
Contains Sensitive Content | Does not contain sensitive content |
ANZSRC Field of Research 2020 | 400199. Aerospace engineering not elsewhere classified |
Public Notes | There are no files associated with this item. |
Funder | Air Force Office of Scientific Research |
Byline Affiliations | University of Southern Queensland |
https://research.usq.edu.au/item/v4x8y/pitching-model-with-control-surface-in-hypersonic-flow-short-duration-ground-tests-and-simulations
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