Laser ignition application to cryogenic propellant rocket thrust chambers

Abstract

Promising a number of advantages compared to existing ignition systems, the use of focused laser light to generate a spark for ignition in rocket combustion chambers has been studied around the world for several years now. At Airbus Safran Launchers, the experimental activities demonstrate the use of a laser-based ignition system in cryogenic liquid rocket engine while taking into account the typical requirements and constraints of a flight mission. The work performed at Airbus Safran Launchers addresses the integration of a laser ignition source into an existing liquid rocket engine. The demonstration activities focussed on the entire range of possible applications on the Ariane Launcher family, that is, the lower stage's Vulcain 2 engine with its thrust chamber and the combustion chamber of the gas generator as well as the re-ignitable Vinci upper stage expander engine. The first tests were performed on subscale hardware and proved the feasibility of using a laser ignition system in a rocket combustion chamber. Laser ignition systems were developed and hot fire tested for the application in full scale combustion chambers under flightlike operating conditions. In the first test campaign, a laser ignition system was successfully applied in the FLPP expander technology integrated demonstrator (ETID), which comprises several technologies for future cryogenic upper stage thrust chambers in the 120 kN thrust class. In a subsequent campaign two different laser ignition systems were used to demonstrate their maturity for the application in the gas generator of the Vulcain 2 engine.