FireStar Foundation Drive
Miles Space / RocketStar
Water-fueled pulsed plasma electric thruster in a 1U form factor for smallsat orbit raising, phasing, de-orbit and attitude control.
Typed specifications9 values
Discloses 6 of 10 fields engineers filter by in this category (category median 3).
- Propulsion family
- electric fusion-enhanced pulsed plasma · datasheet p.2
- Mass
- 980 g product page
- Thrust
- 2.9 mN product page 17.6 mN
- Envelope (L×W×H)
- 95 x 95 x 95 mm (1U with 5 mm margin) product page
- Specific impulse
- 7 300 s product page
- Total impulse
- 17 800 N·s product page
- Propellant
- water product page
- Survival temperature
- -40 °C product page
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 supplier17 lines, in the manufacturer's own wording
- Propellant
- H2O (filled as liquid; liquid or solid during storage/use)
- Envelope
- 95 x 95 x 95 mm (1U with 5 mm margin)
- Wet mass
- 980 grams
- Propellant load
- 250 grams of liquid, pure water
- System power
- 6 Watts (typical, all thrusters active)
- Max system power
- 18 Watts (maximum, all thrusters active)
- Thermal draw
- 11.5 Watts (heater on, no thrusters active)
- Operating temperature
- -25C to +49C (valves heated to 4C)
- Survival temperature
- -40C to 49C
- Supply voltage
- 5 V logic, 12 V thrust
- Thrust
- 17.2 mN (all thrusters active)
- ISP
- 7,300 sec
- Total impulse
- 17,800 Ns
- Delta v
- 4,620 m/s for 4 kg 3U; 2,273 m/s for 8 kg 6U
- Thrust/power
- 2.9 mN/Watt
- Thrust/mass
- 17.6 mN/kg
- Design life
- >= 4x propellant load (based on ongoing experiments)
About
The FireStar Foundation Drive is RocketStar’s (formerly Miles Space) baseline electric propulsion unit, using a pulsed electrostatic cycle to accelerate ionized water vapor and generate thrust. It is packaged in the M1.4/M1.5 form factor with a 1U envelope designed for integration into 3U-and-larger spacecraft. The thruster uses safe, inexpensive, storable water as propellant, split between a plasma formation region with spark electrodes and dual exhaust ports ringed by acceleration electrodes powered by a single supply. It is intended for orbit raising, orbit phasing, de-orbit, drag makeup, reaction-wheel desaturation and attitude control. The thruster has demonstrated operation with multiple propellant gases including water vapor, xenon, argon, krypton, iodine and air, and is ready for delivery, with units manifested to fly on D-Orbit’s ION Satellite Carrier via SpaceX Transporter rideshare missions in 2024.
Documentation
Need the full ICD, test reports or a specific revision? Ask the supplier directly.