Description: 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.

Benefits: 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

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