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Improved Ignition for Low-Cost, Non-Toxic Hybrid Propulsion Systems
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Description
Install and test several advanced ignition methods for a small Nitrous Oxide Hybrid de-orbit propulsion system built at JSC.
Benefits
Hybrid de-orbit can be accomplished with pyro-based ignition, but would benefit from modern electronics capabilities. Alternate igniton system could be broadly applicable to any propulsion need that requires medium performance combined with re-start capability, low development cost, non-toxic chemistry and ease of manufacture.
Details
| Technology area | Propulsion Systems > Chemical Space Propulsion > Hybrids |
| Program | Agency Independent Research and Development (A-IRAD) |
| Lead organization | Johnson Space Center, Houston, TX |
| Start date | 2025-11-01 |
| End date | 2026-09-30 |
Project contacts
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How to get involved
This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.
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