Ignition of green propellant rocket thrusters using a miniaturized high energy laser

Kurzfassung

State of the art RCS thrusters like cold gas and hypergolic-propelled thruster do not need ignition systems. Due to high handling costs, an increasing demand for environmentally friendly systems induces research and development activities for alternative propellant options like the non-hypergolic combinations LOX/hydrogen or LOX/methane. These combinations require new ignition sources as the existing igniters are often heavy or cannot achieve reignition which is required especially for RCS thrusters. Due to the high achievable energy densities and high degree of freedom on the ignition spot location, laser-based igniters are well suited for the ignition of green propellants. During the last years the laser ignition system (LIS), originally developed for the ignition of automotive engines, has reached a sufficiently high level of stability and miniaturization to enable competitive operation on space craft engines [1,2].