RAVEN SPACE SYSTEMS, INC. — National Aeronautics and Space Administration STTR Phase I: T12

Description

To automate the fabrication of ablative Thermal Protection Systems (TPS), a novel in-situ curing additive manufacturing (AM) technology and high-performance composite materials will be developed. The state-of-the-art in-situ curing nozzle utilizes localized volumetric heating of the extrudate to rapidly cure the polymer and adhere it to the flight structure. Rollers following the thermoset printhead will consolidate the materials reducing voids and eliminating previously necessary repairs on fabricated TPS before launch. The composition of the composite materials will be easily varied to gradient the material properties through the thickness of the TPS. Highly insulative materials closer to the flight structure and highly structural materials closer to the stagnation point of the vehicle will be critical for high-performance TPS. Future implementation of a continuous fiber 3D printhead will allow printing of the honeycomb or iso-grid reinforcement to stop potential crack propagation in high shear environments. Additionally, a highly robust outer layer of continuous carbon fiber will be 3D printed on the TPS for enhanced mechanical reinforcement. The unique combination of the novel in-situ curing nozzle, high-performance thermoset composite materials, and a multi-axis robotic arm will enable automated and time-efficient fabrication of TPS with minimal defects. This technology will facilitate future NASA missions to the Moon and Mars by initializing an assembly line for atmospheric entry vehicles of the future.nbsp;