Dynamic Wind Tunnel Testing of an Actuated Canard-Controlled Hypersonic Model
Paper
Van Hoffen, Morgan. 2024. "Dynamic Wind Tunnel Testing of an Actuated Canard-Controlled Hypersonic Model." AIAA SciTech Forum 2024. Orlando, FL, United States 08 - 12 Jan 2024 United States. https://doi.org/10.2514/6.2024-2888
| Paper/Presentation Title | Dynamic Wind Tunnel Testing of an Actuated Canard-Controlled Hypersonic Model |
|---|---|
| Presentation Type | Paper |
| Authors | Van Hoffen, Morgan |
| Year | 2024 |
| Place of Publication | United States |
| ISBN | 9781624107115 |
| Digital Object Identifier (DOI) | https://doi.org/10.2514/6.2024-2888 |
| Web Address (URL) of Paper | https://arc.aiaa.org/doi/10.2514/6.2024-2888 |
| Web Address (URL) of Conference Proceedings | https://arc.aiaa.org/doi/book/10.2514/MSCITECH24 |
| Conference/Event | AIAA SciTech Forum 2024 |
| Event Details | AIAA SciTech Forum 2024 Event Date 08 to end of 12 Jan 2024 Event Location Orlando, FL, United States |
| Abstract | Controlling hypersonic vehicles is especially challenging due to the complex interactions between vehicle subsystems, the flow field and the flight control logic. Full-scale flight testing is typically the only way to truly validate control system performance, however this can only be performed late in the design process, at significant risk to the hardware and when design changes are very costly. We previously demonstrated the feasibility of conducting closed-loop control experiments in hypersonic wind tunnels, using a canonical pitching wing-plus-flap model. Here, we extend this work to consider a generic hypersonic vehicle geometry free to rotate in pitch or roll, controlled by two independently actuated forward canards. In this work we outline an experimental methodology to measure the dynamic response of the system from on-board sensors and utilise a digital twin of the system to extract the aerodynamic pitching and rolling moments from two wind tunnel tests. By evaluating our numerical simulation at each state along the trajectory, we can compare our predicted and measured moments. Comparison of these results shows good steady-state agreement for the pitch and roll moments, however significant differences occur in transient regions. We attribute these differences to high canard accelerations and resulting oscillations in the experimental hardware. |
| Contains Sensitive Content | Does not contain sensitive content |
| ANZSRC Field of Research 2020 | 400106. Hypersonic propulsion and hypersonic aerothermodynamics |
| Public Notes | There are no files associated with this item. |
| Byline Affiliations | University of Southern Queensland |
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https://research.usq.edu.au/item/z8620/dynamic-wind-tunnel-testing-of-an-actuated-canard-controlled-hypersonic-model
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