The Lockheed Martins N+2 Low-boom Supersonic Commercial Transport (LSCT) aircraft is optimized in this study through the use of a multidisciplinary design optimization tool developed at the NASA Armstrong Flight Research Center. A total of 111 design variables are used in the first optimization run. Total structural weight is the objective function in this optimization run. Design requirements for strength, buckling, and flutter are selected as constraint functions during the first optimization run. The MSC Nastran code is used to obtain the modal, strength, and buckling characteristics. Flutter and trim analyses are based on ZAERO code and landing and ground control loads are computed using an in-house code.
Aeroelastic Tailoring Study of N+2 Low-Boom Supersonic Commercial Transport Aircraft
2015
34 pages
Report
Keine Angabe
Englisch
Civil Engineering , Aircraft , Test Facilities & Equipment , Aeroelasticity , Sonic booms , Supersonic transports , Commercial aircraft , Aircraft design , Design optimization , Multidisciplinary design optimization , Structural weight , Nastran , Buckling , Flutter analysis , Design analysis , Landing loads , Aircraft models , Strength
British Library Conference Proceedings | 2015
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