One promising solution to affordable space exploration beyond the lower Earth orbit lies in advanced tailorable composites and/or hybrid material systems (TC-HMS), which can equip lightweight space structures with reduced thermal sensitivity while retaining their strengths/stiffnesses. In contrast to conventional unidirectional fiber-reinforced composites (UDFRCs), TC-HMS have: Location-dependent stiffness/strength, coupling structural design with material design. Stiffness and strength dependent on both location and stacking sequence. There are still major technical barriers to exploiting the full potential of TC-HMS: Most efforts are aimed at simple structures with special-purpose codes there is a need for theories and codes integrated into commercial codes for the design of real TC-HMS structures. Most approaches are based on the classical lamination theory (CLT) and its refinements, which rely on assumptions applicable to UDFRCs but not necessarily TC-HMS there is a need for more advanced models capable of accurately modeling TC-HMS without ad hoc assumptions. We will develop an efficient high-fidelity design tool for advanced TC-HMS, including: An integrated design framework with user-friendly GUI plug-ins in MSC.Patran/Nastran and Abaqus, exploiting these tools versatile modeling capabilities and ready to be integrated into other commercial codes. A versatile parameterization method capable of expanding the design space for TC-HMS; considering varying fiber orientations, ply coverages, and microscale material selection simultaneously, and accompanied by general-purpose optimizers capable of producing TC-HMS designs with optimized load paths. Mechanics of structure genome (MSG)-based thermomechanical micromechanics and plate/shell models designed to compute the location-dependent stiffness and strength of a TC-HMS; rigorously derived and capable of accurately predicting displacements/strains/stresses due to both loads and temperature changes. Potential NASA Applications (Limit 1500 characters, approximately 150 words): Lightweight structures for satellite buses, landers, rovers, solar arrays, antennas Cryogenic tanks, pressurized habitats (including hatch, access, window cutout features), and other structural components (lander truss cages, landing gears) Next-generation airframe technology (hybrid/blended wing body) Highly flexible wings, highly fatigue/damage tolerant structures for vertical lift aircraft Deployable composite booms, foldable panels, hinges, reflectors Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words): Better engineering and qualification of broader composite lightweight structures (with improved predictive capabilities) Validated design and analysis tools for the industrial realization of tailorable composites (aerospace, energy/wind, auto, marine, etc.) with reduced cost & time Duration: 13
