Novel Instrumentation for Rocket Propulsion Systems

The objective of the proposed SBIR Phase II program is to develop, deploy and deliver novel laser-based instruments that provide rapid, in situ, simultaneous measurements of gas temperature, velocity and mole fractions of several important species in rocket plume exhaust flows at NASA Stennis Space Center. Based on proven laser absorption spectroscopy techniques and successful demonstrations in Phase I, the instrument will employ novel room temperature near-IR and mid-IR lasers to determine the concentrations of several combustion products, pollutants and flowfield parameters (gas temperature and velocity) with high sensitivity. The Phase I instrument will be tested and refined in combustion flows at University of Wisconsin-Madison Engine Laboratory and at LGR and demonstrated in realistic flows at NASA Stennis Space Center. The fast response of the instrument will enable engineers and scientists to record precise measurements of several important gasdynamic parameters in rocket engine (including Space Shuttle Main Engine) flows to identify temperature and species nonuniformities, combustion instabilities and to refine and improve computational models.