We incorporate maneuver load alleviation (MLA), gust load alleviation (GLA), and natural laminar flow (NLF) into aircraft conceptual design. The present work uses physics-based methods to capture the dynamic interplay among the three technologies. The results demonstrate that the simultaneous application of MLA and GLA can tilt the balance of the transonic Mach-sweep-thickness (MAT) trade in favor of high aspect ratio, low-sweep natural laminar flow wings. A minimum cost turbulent aircraft designed concurrently with MLA and GLA control systems can achieve a significant 10% reduction in fuel burn and 3.4% reduction in cost relative to a baseline design without load control. The fuel and cost savings grow to 15% and 5% respectively when we design for NLF. The aeroservoelastic conceptual design framework developed in this thesis can serve as a platform for assessing future aircraft configurations and operational paradigms aimed at reducing aircraft fuel consumption and environmental impact.
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