Hello! I'm Thomas Booska, a 3rd-year mechanical engineering student at Arizona State University, in Tempe, AZ.
Throughout the last 2.5 years, I have worked both on the amateur level as well as professionally, with the operation of professional LOx/LNG propellant feed systems at Blue Origin, and amateur LOx/IPA propulsion/feed systems at ASU, with an emphasis on propulsion test operations and cryogenic fluid systems. I have found a deep love and appreciation for developing and executing test operations in development environments, bringing up new systems and engines through their first phases of life, and large-scale propulsion development testing is where my professional interests lie.
In college, I have devoted my free time to advancing amateur solid rocketry, through developing simplistic design and manufacturing methods of high-speed, low cost, and low part-count solid rockets (Mach 3+). Additionally, in an effort to control variables and increase performance, I have led ASU's solid propulsion research group in the design and manufacturing of propellants and solid rocket motors, and conducted 12 successful SRM firings to date. In my time at ASU, I have conducted 16 solid rocket launches, accrued more than 200,000 feet of cumulative altitude, and broken the Mach 3 barrier on 4 different occasions. I have centered my projects and style of work around the simplification and vertical integration of home-built rockets, with the goal of reducing costs, and increasing launch cadence, reliability, performance, and accessibility.
For any contact, both personal and professional, feel free to reach out using my LinkedIn, Instagram, or by email, at thomasstevenbooska@gmail.com.
Recent Developments
In a team of 2, we recently flew ASU's experimental solid propellant, developed under my lead, for the first time. The 2" diameter rocket featured a custom monolithic propellant geometry and carbon composite motor case, and reached a measured Mach 3.3.
As the ASU liquid propulsion test operations lead, I recently oversaw the test of our 350lbf LOx/IPA system, which completed a nominal hotfire of a liquid rocket engine for the first time in ASU history. The thrust and pressure reached nominal design points, and test operations were executed as expected.