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Long Beach, CA, United States

Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase I | Award Amount: 149.88K | Year: 2015

ABSTRACT:This proposal effort seeks to demonstrate the feasibility of developing a methodology for propagating measurement errors through common modal parameter estimation algorithms and assurance criterion. This effort will leverage existing uncertainty quantification and modal parameter estimation software. Two modal parameter estimation algorithms and two uncertainty propagation techniques will be considered during the Phase I program. An experimental and simulation (finite element) model will be constructed, tested, and analyzed using the proposed methodology. Additionally, the accuracy and efficiency of the proposed tool as well as important feedback and key learning lessons will be reported in the form a feasibility study.BENEFIT:Potential applications will include the use of the developed software to assist in the verification, validation and accreditation (VV&A) of any experimental modal analysis. An additional benefit includes the ability to analyze unit-to-unit variation in any mass produced component where structural dynamic considerations are important. Generic to any system requiring VV&A for experimental modal analysis, the developed software could be utilized by commercial companies such as Boeing, Lockheed Martin, and Northrop Grumman.

Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase II | Award Amount: 749.94K | Year: 2015

Approaches for weight prediction, in the conceptual design phase, typically consist of parametric relations or empirical databases. Historical databases work reasonably well when applied to existing or conventional designs, however, they fail to predict accurately the weights and loads associated with unconventional designs (like the Low Boom Flight Demonstrator). There exists a need to augment existing historical databases with a physics-based methodology/capability for predicting the weights and loads of unconventional designs. In the current proposal, M4 Engineering will continue to streamline the structural layout process, improve the overall user experience, and develop a comprehensive suite of capabilities in an effort to build a complete weight statement for unconventional (and conventional) conceptual wing and fuselage designs. The main goal for this effort will be to develop a software tool capable of generating weight and load responses for unconventional designs from physics-based structural analysis simulations.

Agency: National Aeronautics and Space Administration | Branch: | Program: STTR | Phase: Phase II | Award Amount: 749.82K | Year: 2015

In aircraft design, reducing structural weight is often a prime objective, while various constraints in multiple disciplines, such as structure, aerodynamics and aeroelasticity should be imposed on the aircraft. Therefore, engineers need optimization tools to incorporate the multidisciplinary constraints using appropriate fidelity during the early stages of concept design. Classic structural design of aircraft structures is based on the concept of a "wing box" that uses simple components such as straight spars and ribs, quadrilateral wing skin panels and straight stiffeners. A new design philosophy, using curvilinear SpaRibs has been introduced based on emerging manufacturing technologies such as Electron Beam Free Form Fabrication and Friction Stir Welding (FSW). In those innovative technologies, the wing structure is manufactured as an integrated part instead of using mechanically fastened structural components. This design approach makes it possible to design curved substructure that is a hybrid between spars and ribs, therefore called "SpaRibs". These can be designed to have favorable coupling between bending and torsion, and can improve the buckling resistance of local panels. The ability to tailor the bend-twist coupling has been shown to offer substantial improvement in aeroelastic behavior without a weight penalty (or alternately, a weight savings without aeroelastic problems). In this program we will advance this technology to a TRL of 5-6 (or to 6-7 in a Phase III) by designing a subsonic transport wing with better aeroelastic and aeroservoelastic performance, and by designing a test article and test program suitable for proving the performance benefits in flight.

Agency: National Aeronautics and Space Administration | Branch: | Program: STTR | Phase: Phase I | Award Amount: 124.99K | Year: 2015

We propose the development of a modern panel code for calculation of steady and unsteady aerodynamic loads needed for dynamic servoelastic (DSE) analysis of flight vehicles. The code will be especially tailored to be robust, reliable, and integrated with the NASA Object Oriented Optimization (O3) system through selection of analysis methods, file formats, and computing environment, allowing it to be efficiently applied to numerous problems of interest to NASA and industry.

Agency: National Aeronautics and Space Administration | Branch: | Program: STTR | Phase: Phase I | Award Amount: 124.39K | Year: 2014

We propose development and demonstration of a dynamic aeroservoelastic modeling and optimization system based on curvilinear internal structural arrangements of variable topology. This will allow combined sizing and topology optimization of complete airplane configurations including aeroservoelastic performance.

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