Greenspacesys offers the GS‑10H green rocket propulsion system, a simple, non‑explosive engine that uses a hydrogen peroxide and ethanol propellant blend to cut carbon emissions by up to 50% and reduce lifecycle costs by at least 60% compared with conventional engines. The gas‑pressurized feed eliminates turbopumps, lowering part count and increasing reliability, while its modular design and ability to be stored fully fueled enable rapid, on‑demand launches for small‑sat launchers and LEO mission integrators.
Funding
Funding not disclosed
Founders
Product
Problem
Current small‑sat launch providers rely on conventional rocket engines that are expensive, complex, and use toxic propellants, leading to high launch costs, operational delays, and increased environmental impact. Additionally, stringent debris‑mitigation standards require more reliable and controllable propulsion solutions.
Solution
Greenspacesys delivers a green rocket propulsion system (GS‑10H) that uses a simple, non‑explosive propellant blend of highly concentrated hydrogen peroxide and ethanol. The engine’s design minimizes moving parts and eliminates turbopumps by pressurizing fuel with gas, resulting in higher reliability and reduced integration time. With a specific impulse of 338 s in vacuum and a thrust of 98 kN, the system provides performance comparable to traditional engines while emitting up to 50 % less carbon. Its non‑toxic propellants enable rockets to be stored fully fueled at spaceports, shortening launch preparation and supporting rapid, on‑demand missions. The modular architecture and protected IP allow easy adaptation for both main and kick‑stage applications and for on‑orbit transport uses.
Target Audience
Primary customers are developers of small launch vehicles and LEO mission integrators seeking cost‑effective, environmentally friendly propulsion for primary or kick‑stage applications.
Features
- Propellant chemistry based on 98 % H₂O₂ and 99.9 % ethanol, offering non‑toxic, low‑emission performance
- Gas‑pressurized feed system removes the need for turbopumps, reducing part count and failure points
- Engine dimensions (1.62 m length, 0.86 m width) and mass (≤100 kg) suited for small‑sat launchers
- High‑altitude Laval split nozzle with automatic quality control for optimal performance across flight regimes
- Re‑usable design delivering at least 60 % lower lifecycle cost compared with incumbent engines
- Capability to be stored fully fueled, enabling rapid launch turnaround and on‑orbit refueling concepts