SBIR-STTR Award

An integrated computational environment for multidisciplinary, physics-based simulation and analyses of airbreathing hypersonic flight vehicles will be developed. These vehicles are among the most promising alternatives for the next generation of Highly Reliable Reusable Launch Systems (HRRLS). The proposed work will enable development of models with varying fidelity, incorporating the coupled dynamic elements resulting from the tightly integrated airframe-engine configuration. These will include aero-propulsion and aero-elastic interactions as well as thermal loading. The effect of unsteady aerodynamics and nonlinear phenomena such as shock-shock interaction on vehicle performance will be evaluated. Simple and intuitive models for control design as well as high fidelity models for validation and simulation will be developed. The investigators' extensive experience with multidisciplinary software such as STARS and FLUENT will be an asset in this regard. Rather than creating completely new suit of software the approach proposed here is to develop new software when necessary but also produce codes which will enhance the present capabilities of existing software to handle coupled aero-propulsion as well as aeroelastic effects. The methods and products developed in this effort will significantly enhance the present capabilities for modeling, simulation, and control design, for airbreathing hypersonic flight vehicles.

In Phase I the team completed all scheduled initial efforts, 1) evaluation of relevant current simulation capabilities, 2) development of aero-thermo-elastic-propulsion simulation of air-breathing hypersonic flight vehicles (AHFVs) and other flight vehicles, and 3) generation of a set of recommendations for multidisciplinary simulation capability, as planned. Numerical examples of this capability are also presented herein. In Phase II we propose to complete our ongoing effort in the developmental area and further extend the tasks that will include acoustics. This team will complete development of an independent, Multidisciplinary Design and Analysis (MDA) tool, primarily employing their respective numerical, finite element based, computer codes in disciplines as Aerodynamics, Thermal, Structures, Propulsion, Acoustics, and Controls, among others. The resulting MDA code, designed in modular form, could be effortlessly interfaced with existing commercial or user-provided codes, if desired. Once completed, the code is expected to have extensive applications in the design and analysis of flight vehicles with a TRL level of 6 or so. The NASA SBIR/STTR solicitation emphasizes the area of MDA as a current topic of primary importance for ARMD Fundamental Aeronautics Program, and this proposal is highly relevant to such a solicitation.