MPUC Monopropellant Propulsion Unit for CubeSats
CU Aerospace
High-thrust monopropellant propulsion using proprietary CMP-X ethanol/hydrogen-peroxide blend — safer, lower-cost alternative to hydrazine, >2,000 Ns total impulse.
Typed specifications3 values
Discloses 2 of 11 fields engineers filter by in this category (category median 3).
- Total impulse
- 2 000 N·s min · product page
- Propellant
- ethanol product page HTP (hydrogen peroxide)
Each value is typed with its unit and measurement condition and cites the datasheet page it was taken from. Nothing is guessed: a field that is absent here has not been published by the manufacturer. machine-extracted ✓ checked by NewSpace Market ✓ manufacturer confirmed by the manufacturer.
As published by the supplier6 lines, in the manufacturer's own wording
- Propellant
- CMP-X (ethanol/hydrogen peroxide)
- Flame temperature
- ~900°C
- Demonstrated ISP
- 178 s at 230 mN thrust
- Continuous firing demonstrated
- >50 minutes
- Freeze temperature
- <-33°C
- Total impulse (2-liter MPUC)
- >2,000 N-s
About
CU Aerospace’s MPUC uses CMP-X, a non-detonable, energetic COTS monopropellant formulation with lower thermal load, water-like viscosity, common materials compatibility, and an additively manufactured thruster head. It is designed for customers accepting a modest performance trade-off in exchange for lower cost, easier transportability, fewer range-safety concerns, longer continuous burns, and lower flame temperature (reducing thermal soakback). The thruster/system scales from small CubeSats to greater than tens of Newtons of thrust.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.