Fabio Bendana
Instructor @Ucla Henry Samueli School Of Engineering And Applied Science
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WORK HISTORY
Instructor @Ucla Henry Samueli School Of Engineering And Applied Science
Los Angeles, CA, US
Instructor for an undergraduate- and graduate-level course on Rocket Propulsion Systems (MAE C150R / C250R) in the Mechanical and Aerospace Engineering Department at UCLA• Topics cover: fundamental combustion thermochemistry, mission and trajectory analysis, liquid-propellant rocket engines, solid rocket motors, hybrid rockets, electric propulsion, and more advanced propulsion concepts (nuclear, detonation engines, etc.)
EDUCATION
UC Irvine
Bachelor of Science - BS, Aerospace Engineering
UCLA
Doctor of Philosophy - PhD, Mechanical Engineering
UCLA
Master of Science (M.S.), Mechanical Engineering
UC Irvine
Bachelor of Science - BS, Mechanical Engineering
SKILLS
ABOUT FABIO BENDANA
I am a research scientist within the Propulsion Science department at The Aerospace Corporation. My primary role is to lead research, development, and testing efforts related to the advancement and application of chemical propulsion technology in support of national security and civil space programs. At Aerospace, I serve as the principal investigator on several active experimental efforts related to the advancement of liquid-propellant rocket engines (LRE) and in-space chemical propulsion systems. This includes: characterizing ignition systems (pyrophoric, spark torch igniters) for booster-class and upper-stage engines, evaluating additively manufactured components for LRE applications, investigating frictional-ignition mechanisms in high-pressure oxygen environments, testing small-satellite propulsion systems, and assessing rocket nozzle flow characteristics in vacuum environments.I received my Ph.D. in mechanical engineering from the University of California, Los Angeles (UCLA) under Prof. Mitchell Spearrin, where I developed novel laser-based sensing technologies for advanced reacting flows. While at UCLA, I demonstrated quantitative temperature and species measurements in liquid-propellant rocket combustors above 100 bar, established tomographic thermochemical imaging techniques for assessing hybrid rocket combustion efficiency, and led the development of a high-enthalpy shock tube facility to further understand gas dynamics, radiative heat transfer, and chemical kinetics in extreme environments.
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