The Truss-Braced Wing (TBW) concept, with its high aspect ratio, offers a promising route to increased energy efficiency. This thesis demonstrates the application of large-scale Multidisciplinary Design Optimization to the TBW concept, utilizing gradient-based optimization and physics-based models. The first contribution of this thesis is to examine the effect of wing-strut location on the TBW configuration and identify the optimal strut position for its conceptual design using physics-based solvers. It is important to determine the optimal strut placement based on structural sizing, as reducing drag and structural weight while maintaining aerodynamic efficiency is crucial to conceptual aircraft design. Vortex Lattice Methods are employed, considering wave, viscous, and interference drags, with corrections to mitigate wing-strut interference effects. Structural analysis is based on linear Euler-Bernoulli beam theory, while propulsion analysis uses simplified thrust tables. The second contribution involves applying novel optimization methods to the conceptual design of the TBW configuration. The use of two sub-scale optimization problems followed by a full-scale optimization, a methodology that, to the author’s knowledge, has not been previously applied to the TBW configuration is used to minimize fuel consumption across various mission phases while also addressing structural and constraint analyses involving over 140 design variables and 400 constraints. The analysis and optimization are performed using CADDEE (Comprehensive Aircraft high-Dimensional Design Environment), a software library that integrates all discipline models. Results show an 8% reduction in gross weight and a 9% decrease in fuel consumption compared to the initial design, with all major constraints satisfied.