Low Flame Temperature Monopropellant Propulsion Unit for Cubesats (MPUC)

CU Aerospace (CUA) proposes the further development of an alternative very low-toxicity Monopropellant Propulsion Unit for Cubesats (MPUC) and delivery of anbsp;brassboard MPUC system (TRL 5) which comprises a 150 mN main thruster subsystem (tested to TRL 6) and its TRL 5 feed systemnbsp;at the end of Phase II. CMP-X (CUA Mono-Propellant 10) is a non-detonable yet energetic COTS formulation that possesses many system-level advantages including lower cost (COTS propellant and non-refractory thruster construction), lower thermal load (~950nbsp;C flame temp), water-like viscosity, and common materials compatibility (aluminum, stainless steels, and most elastomers). CMP-X thrusters have demonstratednbsp;180 s specific impulse at 174 mN thrust during thrust stand testing and continuous firing times gt; 10 min.nbsp;Phase I demonstrated an improved catalyst for CMP-X with higher reactivity and longer lifenbsp;with minimal warmup time, enabling scaling to gt;500 mN.nbsp;An earlier, slightly more concentrated formulation (CMP-8) hasnbsp;demonstrated shelf life exceeding 1200 days.nbsp;Phase II studies will include long-duration CMP-X storage testing, UN/DOT Series 6 testing to establish a formal hazard classification of CMP-X (anticipated to be permitted on common commercial air transport such as UPS), further catalyst risk reduction studies / characterizations, and brassboard feed system development.nbsp;CMP-X is designed not for highest performance Isp, but as a monopropellant option for customers who can accept a modest 20% performance penalty (relative to AF-315E and LMP-103S) for the advantages of lower cost, air transportability, considerably fewer range safety concerns, lower flame temperature resulting in considerably less thermal soakback into the spacecraft, and longer continuous thrust burns.nbsp;The estimated total impulse of a 2U-sized flight MPUC is gt;2400 N-sec with a peak power draw of ~6 W and 180 s specific impulse.