Our Products
Propulsion Technologies based on DLR Research
As a spin-off, our propulsion technologies are based on more than 10 years of research and development activities at the German Aerospace Center (DLR).
We offer two different green propulsion technologies: HyNOx and HIP_11:
- The HyNOx propulsion technologie is most suitable for smaller, lighter spacecraft as e.g. cubsats, smallsats or orbital transfer vehicles.
- The HIP_11 technology offers significant advantages for heavier, larger spacecraft as e.g. capsules, landers or large satellites.
If you are interested in a demonstration test campaign or a joint development program:
HyNOx Thruster
- Non-toxic bipropellant with nitrous oxide and ethane
- Low-cost and easy available propellants
- Self-pressurized propulsion system
- Isp up to 300 s
- Thermal steady state operation and pulse mode demonstrated
- Combustion efficiencies up to 96% demonstrated
- Vacuum ignition and steady state operation demonstrated
HyNOx - 22
- Nominal vacuum thrust: 22 N
- Isp: up to 290 s
- Minimum Impulse bit: < 2 Ns
- Single pulse firing time: >15 minutes steady state
- Pulse mode: <100 ms On-Time
- Overall firing time: > 1 hour
- Oxidizer/Fuel Mixture ratio: Between 5 and 40
- Chamber pressure: 2 - 12 bar
- Throttable, thrust range: 35 % - 200 %
- Regenerative Cooling
- Fully 3D-printed design
Available: End of 2023
Demonstrated Performance
HyNOx - 1
Demonstrated performance
- Nominal vacuum thrust: 1 N
- Isp: up to 270 s
- Minimum Impulse bit: < 0.05 Ns
- Single pulse firing time: >3 minutes steady state
- Pulse mode: 50 ms On-Time
- Overall firing time: > 20 minutes
- Oxidizer/Fuel Mixture ratio: Between 5 and 40
- Chamber pressure: 2 - 12 bar
- Throttable, thrust range: 35 % - 200 %
- Regenerative Cooling
Available: Begin of 2024
HyNOx-200
Under Development
Planned Performance
- Nominal vacuum thrust: 200 N
- Isp: up to 300 s
- Minimum Impulse bit: < 20 Ns
- Single pulse firing time: >15 minutes steady state
- Pulse mode: 200 ms On-Time
- Oxidizer/Fuel Mixture ratio: Between 5 and 40
- Chamber pressure: 2 - 12 bar
- Throttable, thrust range: 35 % - 200 %
- Regenerative Cooling
Available: Mid 2024
HIP_11 Thruster
Under development
- Hypergolic propellant based on hydrogen peroxide and an ionic liquid fuel
- Combustion efficiency >96 % demonstrated
- Vacuum ignition demonstrated
- Isp up to 310 s
- Steady state operation and reliable pulsing down to 50 ms demonstrated
200 N thruster available end of 2024
Further thrust classes in 2025
Green Propulsion Systems
based in HyNOx and HIP_11
Tailored propulsion systems for you needs available from 2024 on
© DLR Spin-off Project InSpacePropulsion Technologies. All rights reserved.
Wir benötigen Ihre Zustimmung zum Laden der Übersetzungen
Wir nutzen einen Drittanbieter-Service, um den Inhalt der Website zu übersetzen, der möglicherweise Daten über Ihre Aktivitäten sammelt. Bitte prüfen Sie die Details und akzeptieren Sie den Dienst, um die Übersetzungen zu sehen.