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Cascading Annular Nozzles For Extreme Thrust Densities
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Description
This project proposes a new type of rocket nozzle utilizing a unique combination of contouring and clustering. A small lab available in MSFC/B4205 will be leveraged for cold-flow aerodynamics testing at no additional cost to this project.
Benefits
The goal is to produce an aerodynamically coupled cascade of nested annular nozzles which achieve massive increases in thrust generated per unit volume with comparably minor losses in efficiency.
Details
| Technology area | Propulsion Systems > Chemical Space Propulsion > Cryogenic Propulsion |
| Program | Center Innovation Fund: SSC CIF (SSC CIF) |
| Lead organization | Stennis Space Center, Stennis Space Center, MS |
| Start date | 2025-10-01 |
| End date | 2026-09-30 |
Project contacts
Listed on TechPort itself — the most direct way to ask about this specific project.
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.
None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.