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摘要
This paper establishes the benefits of a truss-braced-wing transonic transport aircraft configuration compared to the cantilever-wing aircraft and to a strut-braced wing. Multidisciplinary design optimization is used to design aircraft with three wing configurations with, increasing complexity of topology: cantilever, one-member truss (strut), and three-member truss. Three objective functions are studied: minimum takeoff gross weight, minimum fuel consumption and emissions, and maximum lift-to-drag ratio. A mission with a 7730 n mile range at a cruise Mach number of 0.85 is considered. The results show the significant advantage of strut and simple truss configurations over the conventional cantilever configuration. One comparison produces a reduction of 45% in the fuel consumption while decreasing the minimum takeoff gross weight by 15%. For a second comparison, the fuel weight is reduced by 33% with a decreased minimum takeoff gross weight of 19%. Very attractive vehicle performance can be achieved without the necessity of decreasing cruise Mach number. The results also indicate that a truss-braced wing has a greater potential for improved aerodynamic performance than other innovative aircraft configurations. Further studies will consider the inclusion of more complex truss topologies and other innovative technologies that are judged to be synergistic with truss-braced-wing configurations.
- 出版日期2010-12
