Enhanced hypersonic aerodynamics and stability models through hardware in the loop ground tests in TUSQ
Abstract
Designing hypersonic vehicles that are both efficient and robust is particularly hard due to the wide operating envelope, the severe operating conditions, and the lack of extensive design heritage. A critical aspect of this process is accurately estimating the aerodynamic performance (Lift, Drag, Moments, etc) and stability margins required for the design. Currently, predictions of aerodynamic performance, damping, and aerodynamic stability of hypersonic vehicles are associated with high levels of uncertainty. These high uncertainties usually mean that design and control approaches are overly conservative, thus limiting the performance of vehicles. Co-design is an approach that allows vehicle design (aerodynamics), trajectory optimisation, and GNC to be considered simultaneously in a systematic way. In this project we will develop a Hardware in the Loop ground test capability to fly controlled hypersonic vehicle models in a short duration hypersonic wind tunnel. Models will be co-designed to perform a single manoeuvre, for example a changein vehicle pose. Experimental data will capture transient aerodynamics and controller performance and provide insight into how these data differ from corresponding simulations. Finally, we will develop a hybrid Gaussian Process Regression (hGPR) model that shows where and how discrepancies exist between simulations and experiment. The hGPR will provide new insight on limitations of simulationapproaches and how these need to be considered in mid-layer control. The project will run in collaboration with FA2389-22-1-4074 Computationally tractable, robust co-design of hypersonic vehicle, which will provide the co-design algorithm. The co-design philosophy was motivated by the opportunity it brings for risk reduction early in the design phase of complex platform solutions, but also asit enables a deeper understanding of the sources of performance limitations. The project sits in the Aerospace Science Research Area 351#Hypersonic Aerothermodynamics, High-Speed Propulsion and Materials, and falls within the research concentration areas Test facilities, instrumentation and diagnostics and Flight performance and control including the influence of non-continuum, non-equilibrium, and aero-thermo-servo-elastic effects. The expected outcomes are new experimental methods, experimental data for controlled vehicle models, improved design and analysis methods, and insight into limitations of simulation approaches and how these need to be considered in controller design. The findings will improve design methods and lead to more performant hypersonic vehicle designs. Outcomes will be disseminated through conference presentations, journal articles, and workshops.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 08, 2024
- Source ID
- N629092412027
Entities
People
- Ingo Jahn
Organizations
- Office of Naval Research
- United States Navy
- University of Southern Queensland