VACCO ArgoMoon MiPS
VACCO Industries
The VACCO ArgoMoon MiPS is a hybrid micro propulsion system combining green mono-propellant and cold gas propulsion for CubeSats, offering attitude control and orbital maneuvering.
Typed specifications46 values
Discloses 7 of 10 fields engineers filter by in this category (category median 3).
- Propulsion family
- cold-gas cold gas part of hybrid MiPS · datasheet p.1 cold-gas cold gas thrusters | chemical green mono-propellant part of hybrid MiPS | chemical green thruster
- Mass
- 1.43 kg max · Dry Mass · datasheet p.1 2.07 kg max · Wet Mass 95% Fill @ 10°C
- Thrust
- 25 mN cold gas thrusters · datasheet p.1 25 mN each cold gas thruster | 100 mN green thruster
- Envelope (L×W×H)
- 92.8 (3.652) x 122.2 (4.812) x 143.5 (5.648) mm datasheet p.2
- Total impulse
- 72 N·s cold gas @10°C · datasheet p.1 72 N·s cold gas thrusters | 72 N·s cold gas, @10°C | 783 N·s green @10°C | 783 N·s green thruster +1
- Propellant
- LMP-103S & R134a datasheet p.1 215 pressurant | 420 propellant | R134a | AF-M315E (HAN)
- Supply voltage
- 9–12.6 V Operating Voltage For Heaters & Valves · datasheet p.1 9–12.6 V Operating Voltage For Telemetry | 9–12.6 V telemetry; heaters & valves
- Power consumption
- 1 W <, for health and status monitoring · datasheet p.1 1 W max · health and status monitoring | 1 W max · Standby Power | 4.3 W max · Thruster Operating Power | 20 W max · Warmup Power
- Data interface
- RS-422 datasheet p.1
- Operating temperature
- 10–40 °C datasheet p.1
- Thruster technology
- monopropellant green (ADN or HAN) 100 mN green thruster · datasheet p.1 cold gas 25 mN cold gas thrusters
- Thrusters in the unit
- 1 100 mN green thruster · datasheet p.1 4 25 mN cold gas thrusters
- Volume
- 1.3 U approximately 1.3U plus the tuna can volume · datasheet p.1
- Propellant mass (full load)
- 420 g tank contains 420 g of propellant (plus 215 g of pressurant) · datasheet p.1
- Feed / tank pressure
- 16.8 bar MDP · datasheet p.1 16.8 bar MDP (244 psia)
- Power at thrust
- 4.3 W max · thruster operating power · datasheet p.1
- Survival temperature
- -34–60 °C datasheet p.1 -34–60 °C non-operating
- Satellite class
- CubeSat datasheet p.1
- Delta-v
- 56 m/s for a 14 kg CubeSat · datasheet p.1
- Power processing unit included
- yes datasheet p.1
- Dry mass
- 1.43 kg max · datasheet p.1
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 supplier7 lines, in the manufacturer's own wording
- Performance density
- 692 N-sec/L
- Green thruster total impulse
- 783 N-sec
- Green thruster delta-v (for 14 kg CubeSat)
- 56 m/s
- Cold gas thrusters total impulse
- 72 N-sec
- Propellant mass
- 420 g
- Pressurant mass
- 215 g
- Power consumption (health and status monitoring)
- < 1 Watt
About
The VACCO ArgoMoon MiPS (Micro Propulsion System) is a hybrid propulsion system that integrates both green mono-propellant and cold gas propulsion technologies into a single unit. This system is designed to provide comprehensive attitude control and orbital maneuvering capabilities for CubeSats. It was notably utilized in Argotec’s ArgoMoon program to achieve high total impulse within a constrained volume, meeting specific mission requirements. The system occupies approximately 1.3U plus an additional ‘tuna can’ volume. It features one 100 mN green thruster, capable of generating 783 N-sec of total impulse, which translates to 56 m/s of delta-V for a 14 kg CubeSat. Additionally, it incorporates four 25 mN cold gas thrusters that collectively produce 72 N-sec of total impulse. Each thruster operates independently, allowing for both delta-V maneuvers and attitude control system (ACS) operations, all managed by an integrated microprocessor controller. Key features include an integral titanium fluid control manifold, low-friction space-grade valves, and an all-welded tank construction. The tank holds 420 g of propellant and 215 g of pressurant. The system also includes an integrated microcontroller and an RS-422 interface for high-level commands from the host spacecraft. It boasts low power consumption, requiring less than 1 Watt for health and status monitoring. The system is easily configurable for different mono-propellants, specifically ADN green (LMP-103S) and Air Force green (AF-M315E).
Documentation
Need the full ICD, test reports or a specific revision? Ask the supplier directly.