Design Optimization of a Truss-Braced-Wing Transonic Transport Aircraft

摘要

This paper establishes the benefits of a truss-braced-wing transonic transport aircraft configuration compared tonthe cantilever-wing aircraft and to a strut-braced wing. Multidisciplinary design optimization is used to designnaircraftwith threewing configurationswith increasing complexity of topology: cantilever, one-member truss (strut),nand three-member truss. Three objective functions are studied: minimum takeoff gross weight, minimum fuelnconsumption and emissions, and maximum lift-to-drag ratio. A mission with a 7730 n mile range at a cruise Machnnumber of 0.85 is considered.The results showthe significant advantage of strut and simple truss configurations overnthe conventional cantilever configuration. One comparison produces a reduction of 45% in the fuel consumptionnwhile decreasing the minimum takeoff gross weight by 15%. For a second comparison, the fuel weight is reduced byn33%with a decreased minimum takeoff gross weight of 19%. Very attractive vehicle performance can be achievednwithout the necessity of decreasing cruise Mach number. The results also indicate that a truss-braced wing has angreater potential for improved aerodynamic performance than other innovative aircraft configurations. Furthernstudieswill consider the inclusion ofmore complex truss topologies and other innovative technologies that are judgednto be synergistic with truss-braced-wing configurations.