SBIR-STTR Award

Austral Engineering and Software, Inc. proposes to develop a methodology and computer tool that uses experimental data to create high-fidelity models for unsteady aerodynamic loading. This approach addresses the need for advanced models that accurately represent loading responses of air vehicles under varied flight conditions. This is particularly important for cost-effective development of uninhabited air vehicles (UAVs) due to their increased agility and autonomy requirements. The Phase I theoretical development consists of two major elements. First is the development of a new indicial response formulation that appropriately reflects the interrelationships between aerodynamic loading and flow mechanisms. In particular, effects of vortex breakdown, critical state crossings, and control surface deflections will be addressed. For critical state crossings, a novel model scheduling approach will be developed. Second, advanced system identification techniques will be used to populate the components of the mathematical formulation. In Phase I, this approach will be validated using the developed software and experimental data to model the body-axis rolling moment of a 65-degree delta wing studied by researchers at AFRL. Military, industrial, academic, and research organizations will be contacted to establish channels for validation during planning and development. Responsive organizations will be the basis for technology transfer and commercialization in Phases II and III.

Austral Engineering and Software, Inc., proposes to develop a methodology and computer tool that uses experimental data to create high-fidelity odels for unsteady aerodynamic loading. This approach addresses the need for advanced models that accurately represent loading responses of air vehicles under varied flight conditions. This is particularly important for cost-effective development of uninhabited air vehicles due to their increased agility and autonomy requirements. The Phase I effort has demonstrated a theoretical connection between nonlinear indicial response formulations and a general nonlinear dynamic system representation. Furthermore, it has been shown tht system identification techniques and model scheduling methods can be combined with experimental data to create mathematical models conforming to the general representation above. This approach can characterize the effects of vortex breakdown, critical state crossings, and control surface deflections, producing a single model that is valid over broad flight envelopes. Phase II will extend the method to multiple degrees methodology. AES will produce a physical model of the UCAV Advanced Technology Demonstration program airframe to obtain wind-tunnel data for validation. Through collaboration with aerospace organizations throughout Phase II, AES with establish commercialization mechanisms for Phase III and beyond.

Keywords:
Aerodynamic Modelsuninhabited Air Vehicles Model Scheduling Nonlinear Techniques Indicial Response T