Ongoing work in ultra-efficient subsonic and supersonic air-vehicles clearly shows the potential of evolutionary and revolutionary concepts to meet the performance goals of future aircraft. With their incorporation of lightweight flexible structures, such configurations may require active/adaptive control systems for load redistribution, flutter suppression and gust load alleviation to ensure reliability and safety. Unfortunately, contemporary analysis methods are unsuitable for aeroselastic and aeroservoelastic analysis of such configurations. Design tools are dependent on low-fidelity approaches that are inadequate for reliably analyzing advanced configurations, whereas CFD coupled to finite element structural models require significant user input to define and support advanced configurations, not to mention extensive computational resources. A new efficient approach that automates the geometry setup, mesh generation, and assembly of fluid-structural coupling interfaces is needed for aeroselastic/aeroservoelastic analysis of conventional and new concepts. To address this critical need, Continuum Dynamics, Inc. proposes the development of a mid-fidelity CFD-based aeroservoelastic analysis to support vehicle design, active/adaptive control effector design and integration, as well as control system development and flight and wind-tunnel testing. Building on CDIs legacy in the relevant disciplines, the project emphasizes technology development to streamline workflows and eliminate user involvement associated with mesh generation and fluid-structural model interfacing to efficiently and accurately undertake full flight envelope vehicle evaluation and optimize when and where to utilize high-fidelity models. Potential NASA Applications (Limit 1500 characters, approximately 150 words): The proposed effort directly supports several NASA projects: the Advanced Air Vehicle Programs Advanced Air Transport Technologies (AATT) project developing the next generation of subsonic and supersonic civil aircraft; the Transformative Aeronautics Concepts Programs Convergent Aeronautics Solutions (CAS) and Transformational Tools and Technologies (TTT) Projects, the integrated Aviation Systems Programs (IASPs) Flight Demonstrations and Capabilities (FDC), as well as the X-56, X-57 and X-59 aircraft. Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words): The proposed effort will produce an aeroelastic/aeroservoelastic analysis to design and evaluate advanced air-vehicle concepts that use structural flexure, novel control effectors and propulsion arrangements for performance enhancement and control. Substantial commercialization opportunities are anticipated from licensing the software and providing related support and engineering services. Duration: 6
