An Integrated Laser Based Rocket Chamber Ignition and Wall Diagnostics System

CFDRC proposes the integration of Laser Induced Breakdown Spectroscopy (LIBS) with its maturing Laser Induced Spark (LIS) technology for rocket chamber and ultimately in-flight engine health monitoring. During Phase I CFDRC and the University of Tennessee Space Institute (UTSI) completed quantitative LIBS measurements of bi-propellant combustion equivalence ratio while simultaneously demonstrating detection of selected trace elements associated with internal chamber erosion. Phase II development efforts will include: (1) The creation of a LIBS property/calibration database and associated measurement procedures for O/F ratio and health monitoring (erosion rate) in an O2/CH4 bipropellant combustion environment, (2) Procurement and assembly of commercial grade laser components into a ruggedized fiber optic based LIBS/LIS system suitable for implementation into an actual launch vehicle environment, (3) Calibration and demonstration of this ruggedized LIBS system within a bi-propellant (LOx – GOx/CH4) combustion chamber; (4) Inference of hot gas wall temperature and heat flux from numerical simulation validated with LIBS atomic species measurements, (5) LIBS/LIS demonstration through single optical access into a laboratory rocket motor. This effort will culminate in the delivery and demonstration of the ruggedized fiber optic coupled LIBS/LIS system at AFRL during a week long seminar effort. CFDRC has teamed with the UTSI to complete all LIBS measurements while strategically collaborating with JP Innovations to ruggedize the Phase II LIBS/LIS system prior to delivery to AFRL. Sponsorship of an Immediate transition of this technology to launch sequence and flight demonstration is anticipated through sponsorship by CFDRC’s customer base.