An Integrated Laser Based Rocket Chamber Ignition and Wall Diagnostics System

Laser Induced Breakdown Spectroscopy (LIBS) has matured to the level that direct measurement of internal rocket engine chamber species and temperatures is feasible. Laser Induced Spark Technology has matured to the level that it is now under consideration as the fundamental ignition source in numerous rocket engine applications. Integration of these technologies into a single system is proposed. Phase I proof of concept demonstration will include: 1. LIBS measurement and OH species and inferred temperatures in a GOx/CH4 combustion chamber at transient ignition and steady state conditions using equivalent laser energy and pulse formatting to an existing laser based ignition system; 2. Utilization of LIBS measurements to validate Large Eddy Simulation (LES) CFD based predictions of chamber species; 3. Inference of hot gas wall temperatures, heat fluxes and velocity profiles of a GOx/CH4 rocket engine using validated CFD based methods; and 4. Identification of commercial grade components suitable for an integrated laser based ignition and diagnostics system within a LOx/CH4 rocket chamber installation. CFDRC has teamed with the University of Tennessee Space Institute and Los Alamos National Laboratory to complete LIBS measurements using laser energy and multiplexing requirements comparable to what is present in a laser based rocket ignition system during Phase I. During Phase II CFDRC will demonstrate this system in a rocket launch environment.