← Back to NASA Technology Projects
Completed TRL 4 (started at 2, targeting 4)
The future Artemis missions are going to expand NASA’s theatre of operations from low-earth orbit to cislunar and deep space environment. For this type of missions CubeSats used as secondary payloads offer great advantages (lower cost, low volume and weight, shorter development time, flexible services such as communication networks, sensors, etc.). CubeSats combined with solid propulsion systems are ideal for space environments, solid propellants provide higher thrust at low volume, driving mass efficiency up, have good long-term storage capabilities making these systems available on demand for lunar system integration. This proposal offers low volume solid propulsion system development by designing a controlled Delta V (ΔV) and attitude control system (ACS) in a smaller volume than typical liquid, hybrid, or gas systems. Typically, ACS and main propulsion are two separate subsystems, this CubeSat-sized concept will use the gases generated by solid propellant in the main chamber to steer the spacecraft. This project would design a system, pursue matching of components with propellant characteristics, identify high-risk items, and procure and plan testing for at least one of them (e.g., high-temperature thruster plenum check-valve). The desired outcomes are to demonstrated testing of high-risk item(s) to show proof of concept, and propulsion-for-sale designs ready for development for 1U to 24U CubeSat’s Mission Application.
Design a CubeSat-sized solid propulsion unit that combines main propulsion and attitude control and explore risk-reduction. The specific objectives are: • Set system mass and performance based on ΔV for different mission requirements (trans-lunar injection (TLI) to high lunar orbit, Gateway to Low (polar) lunar orbit, etc.) • Size and match the components of the propulsion system • Optimize propellant combustion temperature, and/or components for higher temperatures. This technology is well supported by several Space Technology Mission Directorate gaps, mainly by: • STMD-SST-001 (2.2.1) Small Spacecraft – High dV Propulsion for Small Spacecraft. • STMD-SST-007 (2.2.7) Small Spacecraft – Low SWaP-C Deorbit or Disposal Capabilities. CubeSat technology has many upcoming uses in the nascent cis-lunar architectures. The proposed innovation revolutionizes CubeSat propulsion with high-density, high-thrust, space environment-tolerant solid propellant while mitigating its typical downsides.
Listed on TechPort itself — the most direct way to ask about this specific project.
This is early/mid-stage (TRL 4) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.
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.