Project

HEPHAESTUS is the newest bi-liquid rocket engine Focus Project at ARIS. With the backing of ETH Zürich, a team of eight highly committed engineering students seeks to develop a flight-ready rocket engine by improving upon legacy systems.

To enable rapid design iterations and improvements the team will employ additive manufacturing technologies and agile product development methods. As the 4th generation of bi-liquid rocket engine development at ARIS, the idea is to develop a reusable pressure-fed system to soar to the skies by significantly upscaling the thrust while keeping weight to a minimum. Before taking off, many system tests will be conducted on the ground on the test stand, which was inherited from previous projects.

Regenerative Cooling

In the thrust chamber of a rocket engine  prevail temperatures of over 2000 °C which is well above the melting point of any metal. Therefore the HEPHAESTUS Engine circulates the fuel through the walls of the thrust chamber before injecting it into the engine. This not only keeps the engine from failing during a firing but also increases efficiency.

Cryogenic Control Valve

The HEPHAESTUS engine works with ethanol and liquid oxygen, leading to system temperatures below -180°C. These temperatures put large stresses on the components and can even lead to freezing. This compounds with the need to remain as lightweight as possible in order to be able to lift off.

Dynamic Pressure Reducer

In order to maintain propellant tank pressure during operation a Dynamic Pressure Reducer will be developed. The controller can detect system changes and adjust accordingly to ensure optimal performance. However, achieving precise pressure control is a technical challenge that demands careful design and calibration for reliable and safe operation.