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Completed TRL 3 (started at 1, targeting 3)
The idea of this proposal is to build on a NIAC project and investigate using a pourable polymer as a method to create lunar or Mars landing pads. This method promises to greatly lower the preparation required to build a landing pad than current state-of-the-art. Launch and landing pads are necessary to mitigate risks to lander/ascent vehicles, surface assets, and orbital assets from rocket plume ejected regolith. This project will build off of the “Regolith Derived Heat Shield for Planetary Body Entry and Descent Systems with In Situ Fabrication” NIAC work. The NIAC Phase 1 study demonstrated that a thermoset polymer regolith composite material was suitable for use as a reentry heat shield. This CIF adapts the NIAC materials and processes to a landing/launch pad application. Two key technical challenges associated with this project include: 1. Minimizing the amount of polymer binder since it must be supplied from Earth. 2. Reducing the viscosity of the composite material enough so that it readily pours. Specific project milestones include: 1. Develop an RTV/regolith composite material for landing/launch pad applications (NTP + 6 months) 2. Develop a lab scale RTV/regolith mixing/pouring system (NTP + 6 months) 3. Demonstrate the capability by pouring lab scale landing/launch pad test articles (NTP + 8 months) 4. Test the landing pad specimens under an acetylene torch simulated landing/launch conditions (NTP + 10 months) 5. Analyze findings and deliver academic paper (NTP + 12 months)
Numerous landing/launch pad concepts have been proposed and studied in the past. The primarily focus has been on emplaced pavers or slabs of sintered regolith.
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