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Abstract
In the frame of an experimental study conducted to assess the feasibility of laser ignition for implementation on cryogenic reaction and control system and orbital and maneuvering system thrusters, fluid flow structures and phenomena affecting ignition have been examined. This paper presents a qualitative analysis of the impact of preignition pressures, propellant injection conditions and injection phenomena such as flash evaporation, the local chamber flowfield, and propellant mass flow stability on altitude ignition. The use of test sequences and encountered phenomena to control the ignition delay and energy deposition and ignition overpressure is addressed.
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