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An Integrated Laser Based Rocket Chamber Ignition and Wall Diagnostics System
Title: Director/Propulsion&Power
Phone: (256) 726-4800
Email: jls@cfdrc.com
Title: President
Phone: (256) 726-4800
Email: mva@cfdrc.com
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.
* Information listed above is at the time of submission. *