HyPrSpace offers a pressure‑fed hybrid rocket engine that combines liquid‑propellant performance with solid‑motor simplicity, eliminating turbopumps and reducing launch system mass and cost. The engine’s throttling capability and recyclable HDPE solid fuel enable affordable, flexible LEO launch services for payloads up to 235 kg, delivered through modular dedicated, lead‑in, or shared mission options.
Funding
$6.4M 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
Access to low‑cost, flexible launch capability for small satellites is constrained by traditional liquid rockets that require complex turbopumps and extensive ground infrastructure, driving high launch prices and long lead times. Existing solid‑motor solutions lack thrust modulation and efficiency, limiting mission tailoring and payload performance.
Solution
HyPrSpace delivers a scalable hybrid rocket engine that merges the performance and throttling capability of liquid propulsion with the mechanical simplicity of solid motors. The patented, pressure‑fed architecture eliminates turbopumps, reducing part count by up to 30 × and cutting launcher cost by roughly 40 %. An ultra‑thin annular combustion chamber ensures stable fuel‑oxidizer mixing across a wide thrust envelope, while a helium‑pressurised feed system provides reliable oxidizer delivery. The engine uses recyclable HDPE solid fuel and liquid oxidizer, offering safe handling, lower carbon footprint, and the ability to tailor thrust for dedicated, lead‑in, or shared launch services. Customers receive end‑to‑end launch solutions—including flight integration, mission planning, and post‑flight data—through a modular service model that adapts to payload size, orbit, and schedule requirements.
Target Audience
Primary customers are commercial small‑satellite operators, government agencies, and research institutions seeking affordable, responsive LEO launch capability for payloads up to a few hundred kilograms.
Features
- Patented annular combustion chamber delivering high specific impulse with consistent efficiency from lift‑off to orbit.
- Pressure‑fed helium oxidizer system that removes the need for turbopumps, reducing system mass and cost.
- Turbopump‑less design with ~30 × fewer components, lowering failure risk and simplifying supply‑chain logistics.
- Thrust‑modulation capability enabling precise trajectory control and multi‑orbit mission profiles.
- Use of recycled HDPE solid fuel combined with liquid oxidizer for safe storage, low‑hazard operation, and reduced carbon impact.
- Modular launch service options (dedicated, lead, shared) supporting payloads up to 235 kg to Low Earth Orbit.
- Proven hot‑fire testing and validated flight‑ready engine demonstrators (e.g., Terminator 1.0).
- Integrated data pipeline delivering mission analytics and compliance reporting to customers.