Pyrophoric ignition system development for hybrid rocket motors in space applications

Hybrid motors are gaining attention in space applications due to their advantageous features like inherent safety and controllability, standing out against conventional solid and liquid engines. However, achieving rapid and reliable ignition remains a significant challenge for hybrid motors, particularly for their use in space systems. Among the various ignition methods, pyrophorics show promising characteristics. In this thesis, ignition delay characteristics of a pyrophoric liquid triethylaluminum (TEA) with nitrous oxide (N2O), a commonly employed self-pressurizing oxidizer, has been investigated for impinging jets, and the feasibility for an ignition system has been evaluated. A series of experiments were conducted to determine ignition delay values and ignition boundaries for two different oxidizer-to-fuel (O/F) ratios by changing the impingement angle. Results have demonstrated relatively favourable TEA/N2O ignition delays across varying impingement angles. This research also comprehensively evaluates experimental outcomes, post-test equipment conditions along with the theoretical aspects to outline the design criteria for a comprehensive ignition system.