FIREHORN
Firehorn is the EPFL Rocket Team’s inaugural cryogenic bi-liquid rocket, operating on an innovative architecture. Anticipated to embark on its maiden 9km flight in late 2025 as part of the European Rocket Championship Competition, it is designed from the ground up with the constraints of a 30km flight, which should occur during 2026.
The project’s aim is to develop a scalable bi-liquid launch vehicle architecture, validating its design through launches at both 9 and 30km altitudes—a step towards our goal of reaching space.
One of the significant milestones to our journey was the project’s PDR (Preliminary Design Review) held in March, where stakeholders were presented with the initial vehicle design. A comprehensive PDR documentation, covering the technical design and project management details since September, totaling 267 pages, has been sent to stakeholders. In parallel, work on assembling a preliminary CAD model of the Firehorn rocket is underway, providing a tangible visualization of previously abstract technical requirements.
Nosecone
Made from CFRP (Carbon Fiber Reinforced Polymer), the nosecone houses the payload and supports the Acoustic Levitation Scientific Experiment. CFRP provides high strength and low weight.
Recovery Bay
Constructed with CFRP, this bay contains the reefed parachute and is designed to handle over 30g deceleration forces.
Avionics Bay
Built with GFRP (Glass Fiber Reinforced Polymer), this section includes omnidirectional antennas and the flight computer for controlling the rocket.
Pressurant Bay
Equipped with a 400-bar COPV (Composite Overwrapped Pressure Vessel) and a Bang-Bang Pressure Regulator to manage pressure during flight.
Tanks
Made of 2050 and 2195 aluminium, the tanks are rated for over 60 bar operational pressure. CFRP aerocovers protect external plumbing, and integrated flight cameras monitor the system.
Internal Structure
The internal structure includes CFRP rods, anti-buckling rings, and 3D-printed interface rings for added support and durability.
Engine Bay
Home to the 7.5kN Ethanol-Liquid Oxygen engine, this bay features cryogenic-rated plumbing, valves, and CFRP fins. It interfaces with the ground segment for launch operations.
