- Type:
- Propulsion
- Lead Time:
- 6 months
- Thrust Range:
- 0.33 N to 1 N (temperature dependant)
- Regulatory:
- ITAR free and REACH compliant
- Propellant Type:
- Nitrous oxide (N2O) and propene (C3H6)
- Specific Impulse:
- >285 s
- .:
- Cold-start capable. No preheating catalysts
- Operating Temperature Range:
- 0°C to 30°C
- .:
- No propellant degradation over time
- Nominal Power Consumption:
- 12.5 W
- Minimum Impulse Bit:
- 35 mN.s
- Minimum impulse bit, cold-gas:
- <20 mN.s using N2O; <2 mN.s using C3H6
- Thrust Vector Control:
- 2-axis
- Delta-v:
- >230 m/s (for typical 3U CubeSat)
- .:
- No thruster degradation over time
- Flow Rate:
- Oxidizer at 170 mg/s; Fuel at 18 mg/s
- Proof Pressure:
- Oxidizer at 110 bar; Fuel at 40 bar
- Burst Pressure:
- Oxidizer at >150 bar; Fuel at >55 bar
- Self-pressurizing propellants: No helium pressurisation systems required. This enables simple, lightweight and low-cost feed system and tank designs. Stable pressure throughout the satellite’s life ensures constant thrust and Isp of >285 s.
- Commonly available propellants: They can be sourced from local industrial gas suppliers and are not subject to export control restrictions. They are REACH compliant and ITAR free.
- Electric based ignition: No preheating of catalysts results in significant power savings. It also means thrusters are rapidly cold-start capable, with unlimited cold-start capability.
- Thrusters fire in both ambient and vacuum environments: Combined with non-toxic propellants, this allows for simple satellite integration and highly representative hardware testing at system level with live or simulated propellants without the need for specialised testing environments.
- Thrusters operate in both hot and cold-gas modes: This means the same thruster can perform both high-performance burns and fine impulse manoeuvres.
- Low power draw: with an average firing power of 12.5W per thruster while firing.
- 6 DOF capable: through a fully integrated RCS system.
Launched on SpaceX’s Falcon9, Arianespace’s Vega and Roscomos’ Soyuz-2 rideshare missions, Dawn’s ECSS qualified, CubeSat Propulsion Modules provide high thrust and high efficiency to get your CubeSat to where it needs to be.
Using non-toxic propellants in a self-pressurizing configuration, these points are unique to Dawn’s green chemical propulsion architecture and enable increased satellite capabilities compared to hydrazine, LMP-103S (ADN), AF-M315E (HAN) or other proprietary fuel-blend systems:
Dawn can deliver complete turn-key propulsion systems, complete with thrusters, propellant tanks, feed system and thruster control electronics. A full-service partner, Dawn provides support in hardware, logistics, systems integration, propellant sourcing and onsite fueling.
| Size | Total Impulse | Dry Mass | Wet Mass |
| 0.7U | >425 N.s | 1000 g | 1170 g |
| 1U | >850 N.s | 1100 g | 1410 g |
| 1.5 U | >1,800 N.s | 1500 g | 2250 g |
Dawn CubeSat Propulsion Module
Dawn AerospaceLaunched on SpaceX’s Falcon9, Arianespace’s Vega and Roscomos’ Soyuz-2 rideshare missions, Dawn’s ECSS qualified, CubeSat Propulsion Modules provide high thrust and high efficiency to get your CubeSat to where it needs to be.
Using non-toxic propellants in a self-pressurizing configuration, these points are unique to Dawn’s green chemical propulsion architecture and enable increased satellite capabilities compared to hydrazine, LMP-103S (ADN), AF-M315E (HAN) or other proprietary fuel-blend systems:
- Self-pressurizing propellants: No helium pressurisation systems required. This enables simple, lightweight and low-cost feed system and tank designs. Stable pressure throughout the satellite’s life ensures constant thrust and Isp of >285 s.
- Commonly available propellants: They can be sourced from local industrial gas suppliers and are not subject to export control restrictions. They are REACH compliant and ITAR free.
- Electric based ignition: No preheating of catalysts results in significant power savings. It also means thrusters are rapidly cold-start capable, with unlimited cold-start capability.
- Thrusters fire in both ambient and vacuum environments: Combined with non-toxic propellants, this allows for simple satellite integration and highly representative hardware testing at system level with live or simulated propellants without the need for specialised testing environments.
- Thrusters operate in both hot and cold-gas modes: This means the same thruster can perform both high-performance burns and fine impulse manoeuvres.
- Low power draw: with an average firing power of 12.5W per thruster while firing.
- 6 DOF capable: through a fully integrated RCS system.
Dawn can deliver complete turn-key propulsion systems, complete with thrusters, propellant tanks, feed system and thruster control electronics. A full-service partner, Dawn provides support in hardware, logistics, systems integration, propellant sourcing and onsite fueling.
| Size | Total Impulse | Dry Mass | Wet Mass |
| 0.7U | >425 N.s | 1000 g | 1170 g |
| 1U | >850 N.s | 1100 g | 1410 g |
| 1.5 U | >1,800 N.s | 1500 g | 2250 g |
- Type:
- Propulsion
- Lead Time:
- 6 months
- Thrust Range:
- 0.33 N to 1 N (temperature dependant)
- Regulatory:
- ITAR free and REACH compliant
- Propellant Type:
- Nitrous oxide (N2O) and propene (C3H6)
- Specific Impulse:
- >285 s
- .:
- Cold-start capable. No preheating catalysts
- Operating Temperature Range:
- 0°C to 30°C
- .:
- No propellant degradation over time
- Nominal Power Consumption:
- 12.5 W
- Minimum Impulse Bit:
- 35 mN.s
- Minimum impulse bit, cold-gas:
- <20 mN.s using N2O; <2 mN.s using C3H6
- Thrust Vector Control:
- 2-axis
- Delta-v:
- >230 m/s (for typical 3U CubeSat)
- .:
- No thruster degradation over time
- Flow Rate:
- Oxidizer at 170 mg/s; Fuel at 18 mg/s
- Proof Pressure:
- Oxidizer at 110 bar; Fuel at 40 bar
- Burst Pressure:
- Oxidizer at >150 bar; Fuel at >55 bar
- Self-pressurizing propellants: No helium pressurisation systems required. This enables simple, lightweight and low-cost feed system and tank designs. Stable pressure throughout the satellite’s life ensures constant thrust and Isp of >285 s.
- Commonly available propellants: They can be sourced from local industrial gas suppliers and are not subject to export control restrictions. They are REACH compliant and ITAR free.
- Electric based ignition: No preheating of catalysts results in significant power savings. It also means thrusters are rapidly cold-start capable, with unlimited cold-start capability.
- Thrusters fire in both ambient and vacuum environments: Combined with non-toxic propellants, this allows for simple satellite integration and highly representative hardware testing at system level with live or simulated propellants without the need for specialised testing environments.
- Thrusters operate in both hot and cold-gas modes: This means the same thruster can perform both high-performance burns and fine impulse manoeuvres.
- Low power draw: with an average firing power of 12.5W per thruster while firing.
- 6 DOF capable: through a fully integrated RCS system.
Launched on SpaceX’s Falcon9, Arianespace’s Vega and Roscomos’ Soyuz-2 rideshare missions, Dawn’s ECSS qualified, CubeSat Propulsion Modules provide high thrust and high efficiency to get your CubeSat to where it needs to be.
Using non-toxic propellants in a self-pressurizing configuration, these points are unique to Dawn’s green chemical propulsion architecture and enable increased satellite capabilities compared to hydrazine, LMP-103S (ADN), AF-M315E (HAN) or other proprietary fuel-blend systems:
Dawn can deliver complete turn-key propulsion systems, complete with thrusters, propellant tanks, feed system and thruster control electronics. A full-service partner, Dawn provides support in hardware, logistics, systems integration, propellant sourcing and onsite fueling.
| Size | Total Impulse | Dry Mass | Wet Mass |
| 0.7U | >425 N.s | 1000 g | 1170 g |
| 1U | >850 N.s | 1100 g | 1410 g |
| 1.5 U | >1,800 N.s | 1500 g | 2250 g |