Lead: Jonas Klein, Julia Rinne, und Manuel Schlüsener

What we do:

In addition to developing a CubeSat, we have set ourselves the goal of developing, building and operating our own experimental rockets.

The focus is on deepening the theoretical knowledge that is taught in lectures at the TU Darmstadt and expanding it to include a practical part. The complex overall system „rocket“ is not only ideally suited to imparting content to our members, but also the indispensable cooperation in an interdisciplinary team. The work should ultimately lead to breaking the European altitude record of 32 km for rockets developed by students.

So far:

The Athena 0 Project was our first rocket generation. Powered by a water jet accelerated under a pressure of 20 bar from the tank into the environment, Athena 0 mainly served as a test vehicle. At low costs, we researched and tested avionics/telemetry, recovery by parachute, attitude stabilisation and pressure tank construction. So far we have launched our Athena 0.1 and Athena 0.2 rockets.

Current Rocket Developement:

The Fantastic Rocket of Darmstadt Origin FRoDo is our newest Rocket generation. It is going to be a solid-propellant rocket with which we are planning to take part at international student rocketry competitions such as EuRoC. At EuRoC, which is promoted and organized by the Portuguese Space Agency the competing University teams will launch rockets to heights from 3000m up to 9000m.

To be able to also compete in such an event we are always looking for motivated students of all disciplines and semesters. If you have any questions about the rocket team, please contact section leader Jonas or Linus.

Long term project:

The long term goal of the rocket team is the developement of a experimental rocket powered by a specially developed liquid propellant rocket engine. The propellants used are ethanol and nitrous oxide, also known as laughing gas. These represent a suitable compromise between performance and easy and safe handling. The engine is designed to develop a thrust of 2 kN at a combustion chamber pressure of 21 bar. To achieve this, the composite tanks must withstand an internal pressure of about 40 bar and an oxidant temperature of -70°C. The Propulsion Subsection is currently working on the engine developement for that rocket.


Then just drop by one of our meetings without obligation. Our weekly project meeting takes place on our Discord Server on Tuesday (even calenderweek) or Wednesday  (odd calenderweek) at 6:00pm.