Juno Propulsion develops advanced rocket engines utilizing rotating detonation engine (RDE) technology for improved space access. This detonation-based combustion method achieves higher specific impulses compared to traditional engines, significantly boosting fuel efficiency. The resulting propulsion systems enable missions to carry twice the cargo to space and enhance satellite performance and defense targeting speed.
Funding
$380K raised to dateRaised to date based on public sources. This may differ from the amount the company actually raised and is based only on what is publicly available on the internet.
Founders
Product
Problem
Current rocket engines rely on combustion methods developed in the 1950s, limiting the potential for increased payload capacity, reduced carbon emissions, and more ambitious space missions. These traditional engines lack the fuel efficiency needed to unlock the full potential of the growing space market.
Solution
This startup is developing rotating detonation engines (RDEs) that utilize a detonation-based combustion method to achieve higher specific impulses compared to traditional rocket engines. Detonation waves rotate around the engine, explosively burning fuel and oxidizer, releasing more energy and increasing fuel efficiency. This technology enables clients to double cargo to space, reduce carbon emissions, increase satellite payload capacity and lifespan, and enable missions to the Moon and Mars. By bringing rocket engines into the 21st century, the company aims to significantly reduce launch costs and increase payload capacity.
Target Audience
The primary target audience includes space launch companies, satellite manufacturers, and space agencies seeking to improve propulsion efficiency and reduce the cost of space access.
Features
- Rotating detonation engine technology using detonation waves for combustion
- Higher specific impulse, resulting in greater fuel efficiency
- Reduced propellant mass flow, lowering launch costs
- Increased payload capacity for rockets and satellites
- Potential for reduced carbon emissions during launch