NASA SBIR 2009 Solicitation
FORM B - PROPOSAL SUMMARY
||Aircraft Systems Analysis, Design and Optimization
||Design Environment for Multi-Fidelity and Multi-Disciplinary Components
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Mechanical Solutions, Inc.
11 Apollo Drive
Whippany, NJ 07981 - 1423
PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
11 Apollo Drive
Whippany, NJ 07981 - 1423
(973) 326-9920 Extension :125
Estimated Technology Readiness Level (TRL) at beginning and end of contract:
TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Many of the most challenging categories of propulsion system development are related to the prediction of interacting effects between the fluid loads, thermal loads, and the structural deflection. In practice, the interactions between technical disciplines are often not fully explored analytically, and the analysis in one discipline often uses a simplified representation of other disciplines as an input or boundary condition. For example, the fluid forces in an engine generate static and dynamic rotor deflection, but the forces themselves are dependent on the rotor position and its orbit. A typical design practice might involve predicting the fluid and thermal loads for various conditions and passing those estimates along for inclusion with the structural model. This practice ignores the interaction between the physical phenomena where the outcome of each analysis can be heavily dependent on the inputs (i.e., changes in flow due to deflection, changes in deflection due to fluid forces). Such a rigid design process also lacks the flexibility to employ multiple levels of fidelity in the analysis of each of the components.
In this project, Mechanical Solutions, Inc. (MSI) proposes to extend two existing software tools to develop a design environment with both breadth (to cover multiple disciplines) and depth (to cover multiple levels of fidelity).
POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
By providing an integrated framework for turbomachinery analysis, the work in this project will reduce the time and complexity of the multiphysics analyses (job setup, solution control, pre- and post-processing). This work directly addresses NASA design environment goals as engineering teams will have the capability to employ multi-fidelity physics-based tools to reduce the failure rate and development cost of propulsion systems.
In this proposed work, the extension of CoMAT to work with NPSS will enhance the capabilities of both tools, and will facilitate a broader range of multi-fidelity, multi-disciplinary analyses and simulations of complete vehicle systems. The numeric zoom functions in NPSS will be enhanced with the fluid-structure interaction capability of CoMAT. Similarly, the high-fidelity analysis in CoMAT will be leveraged by the high level functions in NPSS. Since both tools are built to work with proprietary and 3rd party solvers, MSI is confident of the commercialization potential of this work.
POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The accomplishment of all Phase I objectives will demonstrate the significant benefits of the combined multi-fidelity / multi-disciplinary design environment. This capability would be immediately useful for the design and development of civilian and military gas turbine engines. Such an analytical capability will also assist the wider turbomachinery community with avoidance of advanced designs, leading to a successful commercialization of the new tool.
NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.
TECHNOLOGY TAXONOMY MAPPING
Feed System Components
Fundamental Propulsion Physics
Simulation Modeling Environment
Structural Modeling and Tools
Form Generated on 09-18-09 10:14