Laser Ignition of Hydrocarbon Rocket Engine Combustion Chambers

Phase I research successfully: 1) demonstrated a prototype fiber-optic coupled laser initiator, 2) analytically and experimentally characterized a single element GOx/CH4 laser ignition process and 3) assessed commercial grade optics/windows, including structural/thermal evaluation of an in-chamber window installation assembly. Phase II will focus on replacing existing squib ignition technology culminate in the launch and recovery of a commercial rocket equipped with a prototype land ser based ignition systems. Specific Phase II development will include: 1. Demonstration of a field configured fiber optic coupled laser initiator capable of immediate implementation into numerous launch vehicle operations. 2. Integration of the initiator and optical transmission devices into an operational bipropellant rocket combustion chamber. 3. Field test and evaluation of laser based ignition through the launch of a Prospector rocket. 4. Assessment of the laser apparatus in a diagnostics mode. CFDRC has teamed with Los Alamos National Laboratory and Garvey Spacecraft to assure all of the technical elements necessary to launch a cryogenic LOx/hydrocarbon fueled rocket are in place at project outset. This Phase II project will effectively increase laser ignition of rocket engines from a current TRL level of 3 to a level of 8. When successful, CFDRC has secured commitments from all liquid rocket propulsion engine and launch vehicle manufacturers to immediately begin implementing this technology into existing and future rocket launch environments.