Student Hybrid Thruster Testing and Research

After the first student-hybrid-thruster campaign at DLR Lampoldshausen in 2011 the Institute of Space Propulsion consequently developed the student-test program. A stronger and improved test rig was fabricated, advanced measurement techniques were applied, more detailed test objectives were defined and testing was accompanied by advanced CFD and thermochemical calculation. In many ways the hybrid thruster appears as an ideal research object for rocket propulsion students. The thruster provides aspects of liquid propulsion, phase transition, solid propulsion, ignition, combustion and rocket nozzle flow. System pressure and combustion temperature are in the order of the state of the art of rocket engines, but for all this the students can fully handle the thruster, rig and testing by their own due to small mass flow and short test duration. Nevertheless the students are introduced to working principles and standards for rocket engine test facilities. The latest test campaign focused on the investigation of the exhaust jet. The experimental studies and advanced measurements were compared to a numerical Navier-Stokes calculation of the flow field