Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase II | Award Amount: 599.98K | Year: 2010
One of the main attributes contributing to the competitiveness of rotorcraft, is the continuously increasing expectations for passenger comfort which is directly related with reduced vibration levels and reduced interior noise levels. Such expectations are amplified in the VIP market where people are used in the acoustic and vibration levels of civil and executive jets. One of the most critical excitations for interior noise in helicopters is the one from the gearbox. Thus, the structure-borne noise path (i.e. excitation propagating from mounting locations through the fuselage structure to the panels of the cabin and to the interior) must be captured in rotorcraft interior noise computations. This proposal addresses the need stated in the solicitation for developing physics based tools that can be used within a multi-disciplinary design-analysis-optimization for computing interior noise in rotorcraft applications. Currently, there is no robust simulation capability for this type of acoustic simulations. The hybrid FEA method can be used for structure-borne helicopter applications and can be integrated very easily (due to the finite element based model) with models from other disciplines within a multidisciplinary design environment. It combines conventional FEA with Energy Finite Element (EFEA) and it extends the frequency range of applicability of an existing finite element model by converting the elements that model the flexible panels into EFEA type of elements. A seamless Hybrid FEA capability of commercial quality will be developed based on MES' commercial EFEA code. UTRC will participate in the proposed effort for validating the new developments through comparisons to test data for a rotorcraft structure and for providing technical consultancy.
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 99.61K | Year: 2010
Aircraft design is a complex process requiring interactions and exchange of information among multiple disciplines such as aerodynamics, strength, fatigue, controls, propulsion, corrosion, maintenance, and manufacturing. A lot of attention has been paid during the past fifteen years in the Multi-disciplinary Design Optimization (MDO) nature of the aircraft design process. However, a consistent void in aircraft design is the ability to integrate high-fidelity computational capabilities from multiple disciplines within an organized MDO environment. Integrating high fidelity simulation technology (that has been developed over the years though significant investments) within a MDO environment will constitute a disruptive technological development in aircraft design. The ability to replace time consuming solvers with metamodels within the highly iterative environment of an integrated network of optimizations is critical for engaging high fidelity simulation tools in the MDO analysis of complex aircraft systems. Previous work completed by the proposing firm has demonstrated the feasibility of conducting such MDO analysis for an aircraft system, while considering outer mold line shape optimization and structural sizing simultaneously. Since the ability to create metamodels from results obtained at a number of sample points from the actual solvers is the key enabling factor for conducting the multi-discipline optimization analysis, the proposed project will use as foundation the existing metamodeling capability of the proposing firm and will pursue new research that will lead to the development of a powerful stand-alone commercial product for metamodel development. The latter, along with the proposing firm's MDO solver will provide the means for operating an integrated network of optimizations for designing aircraft systems.
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 99.96K | Year: 2008
Aircraft design is a complex process requiring interactions and exchange of information among multiple disciplines such as aerodynamics, strength, fatigue, controls, propulsion, corrosion, maintenance, and manufacturing. A lot of attention has been paid during the past fifteen years in the Multi-disciplinary Design Optimization (MDO) nature of the aircraft design process. However, a consistent void in aircraft design is the ability to integrate high-fidelity computational capabilities from multiple disciplines within an organized MDO environment. Integrating high fidelity simulation technology (that has been developed over the years though significant investments) within a MDO environment will constitute a disruptive technological development in aircraft design. Currently, each high fidelity simulation is rather compartmentalized, and at best a sequential interaction process is exercised. Integrating the high-fidelity computational capabilities from multiple disciplines within an organized MDO environment will provide the ability to capture the implications that design changes in a particular discipline have to all other disciplines. It will also be possible to share design variables among disciplines and thus identify the direction that design variables should follow based on objectives and constraints from multiple disciplines. During the Phase I effort the feasibility of utilizing high fidelity CFD simulations for shape optimization and combining them with a structural finite element simulation for strength considerations within a multi-discipline design optimization environment will be demonstrated. A wing configuration will be analyzed for showcasing the different steps of this development and the benefits.
Agency: Department of Defense | Branch: Navy | Program: STTR | Phase: Phase II | Award Amount: 2.00M | Year: 2008
The Navy needs to design new ships capable of accomplishing complex missions at a reduced cost. In order to enable US military response to threats around the world new ships must be designed with improved operational abilities and with capabilities to integrate with other ships and platforms for maximum operational flexibility. New enabling technology is needed for performing systematic design for optimal performance at three different levels: discipline level for optimizing a particular performance metric for a particular ship (i.e. hydrodynamics, survivability, signatures, seakeeping, etc.); improve the system level objectives for a particular ship (i.e. best operational capabilities as a unit at multiple disciplines for minimum cost); optimizing the system-of-systems level operational performance of multiple ships interacting and operating together as a group. Other elements such as the influence of uncertainty on performance metrics, the lack of detailed information at the upper level mission profile, and the impact of engineering decisions and scheduling on cost must be an integral part of the system of systems design process. The proposed SS-MDO-U system provides this new enabling technology. It will provide a systematic manner for performing physics based design for ships, optimizing individual performance metrics for each ship, and ensuring desirable inter-operational characteristics among ships. This design process will be carried in a cost conscious environment, while reliable performance will be secured in the presence of uncertainty. Finally, the SS-MDO-U system will be linked with the current Naval design tools and the new development will be demonstrated through a comprehensive case study on a topic directly related to Naval interests.
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase I | Award Amount: 149.90K | Year: 2015
ABSTRACT:Advancements in propulsion systems, aerodynamics, and flight control capabilities are enabling hypersonic vehicles to operate at high speeds and altitudes. Therefore, significant new demands are placed on the materials used for constructing a hypersonic system due to the harsh environment created by the high speeds. An integrated design approach that considers the design, the processing, and the selection of the materials simultaneously with the overall design of the vehicle will link the material properties selection to the overall performance of a hypersonic vehicle and constitute a major new enabling technology. In this project the ICMSE modeling and simulation approaches will be investigated and the material selection will be integrated with the decision support environment which is offered by the DS Toolkit. The DS Toolkit offers the ability to determine how the performance metrics and the operational requirements change when the design of the vehicle varies. The DS Toolkit has been employed in the past for hypersonic vehicle design. The new developments will be employed for conducting the material selection, the trajectory analysis, and the thermal protection system (TPS) design simultaneously for a hypersonic vehicle. Thus, the tight integration of the material selection with the overall design process will be demonstrated.BENEFIT:Integrating material selection with product design is of interest to the shipbuilding, automotive, aircraft, space, military ground vehicle, and energy Industry sectors. The common factors among these Industries are: all use multi-physics simulation models for assessing the performance of their products during design; designing materials for cost effectiveness, ease of manufacturing, and enhanced properties is an essential part in new product development; they all have needs for reducing weight and creating fuel efficient systems; they all have multiple and mutual competing performance requirements. In addition, the energy Industry and any powertrain application have similar needs with hypersonic vehicles for materials that exhibit good mechanical properties at high temperatures. Thus, significant benefits will be offered in many Industries by the technology which will be developed by the proposed project.