ISPTech offers not one, but two green propellants. The corresponding technologies are based on more than 10 years of research and development activities at the German Aerospace Center (DLR).

HyNOx

THE SELF-PRESSURIZING PROPELLANT

HyNOx is the combination of nitrous oxide (N₂O) and ethane (C₂H₆). Both of these components are non-toxic, affordable and easily available.

The propellants are stored under saturated conditions in the tanks. They have a high vapor pressure in the relevant temperature range – enabling a simple system architecture. There is no need for a pressurant gas.

HIP_11

THE GREEN HYPERGOLIC PROPELLANT

HIP_11 is a hypergolic propellant combination consisting of highly concentrated hydrogen peroxide (H₂O₂) and an ionic liquid fuel. Compared to conventional hypergolic propellants, it offers similar performance but higher density and significantly reduced hazards.

What we offer

Propulsion for every spacecraft and mission.

HyNOx Propulsion Systems

From standarized CubeSat propulsion units to tailored solutions for your spacecraft – ISPTech offers integrated propulsion systems with thrusters, tanks and control units.

HyNOx Thruster Family

Learn more about our extensively tested HyNOx thrusters – delivering high performance, precision and unlimited impulse bit.

HIP_11 Propulsion Solutions

Thrusters and propulsion systems for our unique hypergolic propellant are currently under development.

HyNOx Propulsion Systems

BUILT FROM STANDARD BLOCKS – CUSTOMIZED FOR YOUR SPACECRAFT

ISPTech develops, tests and supplies propulsion systems for every spacecraft and mission, based on its HyNOx thrusters and proprietary control unit. Propellant tanks and pressure system components are produced by a list of carefully selected suppliers.

Customizable Propulsion Systems

Included hardware	HyNOx thrusters Propellant tanks Feed system with sensors Pressure relief components Fill and drain interface Structural mount to S/C (customized) Heaters Electronic control unit (ECU)
Interfaces	Customized mechanical interface Supply voltage 22-33 VDC (customizable) Communication with ECU via CAN
Services	Thruster acceptance testing and derivation of performance models Propulsion system integration and characterisation Fueling System and tank condition model
Thrust classes	HyNox-200 Thruster (50-400 N) HyNOx-22 Thruster (11-44 N) HyNOx-5 Thruster (2.5-10 N) HyNOx-1 Thruster (0.5-2.0 N) Cold Gas Thrusters
Impulse class	CubeSat Propulsion Systems up to 5,000 Ns Customized Propulsion Systems starting from 5,000 Ns
Performance	up to 290 s for hot gas up to 60 s for cold gas
Temperature range	Thruster operatable for saturated fluid temperatures: -29°C to +32°C System survivability temperature range customizable
Propellant feeding	Liquid or gaseous, depending on mission requirements.
Status	Demonstrator under testing Customer projects ongoing

Request additional information or quote

HyNOx 4U CubeSat Module

ISPTech is currently developing a 4U CubeSat Propulsion System based on its HyNOx-1 thruster – enabling significant deltaV in a short amount of time.

Thrusters	1x HyNOx-1 (0.5-2 N, Isp up to 270 s) 4x Cold / Warm Gas Thrusters
Dimensions	4U (209.3 x 209.3 x 110.0 mm³) Z-length adjustable.
Capabiltites	Up to 4,000 Ns impulse (for standard length). 0.5-2 N thrust for rapid orbit changes Roll, pitch and yaw control
Electronics	24-33 VDC Supply Voltage Communication via CAN bus (other options possible)
Status	Available summer 2025
Lead Time	5 months
Qualification	According to SpaceX Falcon 9 Payload User Guide (e.g. for rideshare missions)

Pre-order now or request detailed specifications

HyNOx Thruster Family

EXTENSIVELY TESTED. STEADY-STATE CAPABLE.

HyNOx thrusters are developed based on years of research at the DLR-Institute of Space Propulsion. The development includes thousands of hot firings under atmospheric and vacuum conditions.

HyNOx-22

Thrust range	11 – 44 N	demonstrated in vacuum
Specific impulse	> 280 s	demonstrated in vacuum
Continous operation	15 min	demonstrated in vacuum, can be increased
Throughput	> 60 kg	demonstrated in vacuum, can be increased
Ignitions	> 4,000	demonstrated in vacuum, can be increased
Minimum impulse bit	< 1 Ns < 50 ms	hot gas, demonstrated in vacuum cold gas
Interface	4x M4	adjustable
Power	10 W 20 W (200 ms) 2W	for ignition flow control valve hit, per valve flow control valve hold, per valve
Mass	< 570 g	including flow control valves
Status	Available now	qualified for NewSpace customer

DATASHEET-HYNOX-22-P03-1Download

HyNOx-1

Thrust range	1 -2 N	demonstrated in vacuum
Specific impulse	> 270 sec	demonstrated in vacuum
Continous operation	15 min	demonstrated in vacuum, can be increased
Throughput	> 1.1 kg	demonstrated in vacuum, can be increased
Ignitions	> 3,000	demonstrated in vacuum, can be increased
Minimum impulse bit	< 50 mNs TBD	hot gas, demonstrated in vacuum cold gas
Interface	4x M4	adjustable
Power	10 W 9 W 0.5 W	for ignition flow control valve hit, per valve flow control valve hold, per valve
Mass	< 200 g	including flow control valves
Status	Available from Q3 2024	Qualification ongoing

Pre-order now or request detailed specifications

HyNOx-200

Thrust range	100 – 400 N	demonstration target
Specific impulse	> 290 sec	demonstration target
Status	available from Q1 2025	in development, atmospheric testing conducted

Request detailed specifications

HIP_11 Propulsion

GREEN AND HYPERGOLIC IS NO CONTRADICTION.

Based on years of basic research at DLR, multiple battleship thrusters for the HIP_11 technology were developed. The current focus is the development of a 200 N HIP_11 thruster.

Interested? Request further information.

Meet us

THE FOUNDERS

Dr.-Ing. Lukas Werling

Co-founder / CEO

Lukas headed a rocket engine test facility and worked for more than 12 years in the field of green rocket propulsion. He has more than 9 years of experience as a group leader and project manager at DLR’s Institute of Space Propulsion. 

During his time at DLR he filed several patents and published more than 40 papers in the field of green rocket propulsion. 

He holds a PhD in Aerospace Engineering from the University of Stuttgart.

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Felix Lauck

Co-founder / CTO

Felix has worked for more than 7 years on green propellants at DLR’s Institute of Space Propulsion.   Felix is an expert on hypergolic ignition and likes to work with hydrogen peroxide.

As PhD project he developed the novel hypergolic propellant combination HIP_11.

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THE TEAM

Julian Dobusch

Lead Engineer HyNOx Propulsion

Robert Rödinger

Propulsion Systems Engineer

Jan Witte

Lead Engineer MAIT

Matthias Haßler

Propulsion Engineer

Florian Merz

Propulsion Engineer

Constantin Bleul

Engineering Intern

Vincent Stratmann

Working Student Propulsion

Coming soon

Coming soon