Linear Burn Rates of Monopropellants for Multi-Mode Micropropulsion
Department
Mechanical and Aerospace Engineering
Major
Aerospace Engineering
Research Advisor
Rovey, Joshua L.
Advisor's Department
Mechanical and Aerospace Engineering
Funding Source
Opportunities for Undergraduate Research Experiences (OURE)
Abstract
A linear strand burner setup was used to obtain linear burn rate characteristics for the mixture of 1-ethyl-3-methylimidazolium ethyl sulfate [Emim][EtSO4] and Hydroxyl Ammonium Nitrate (HAN) . A closed, pressurized system with an Argon atmosphere provided the environment to conductively heat a small cylinder of propellant within a length of quartz tubing through a length of nickel-chromium wire. The initial change and maximum pressure within the system were recorded to calculate the burn time of each test. This process occurred for varying pressures within the range 0-300psig. Open air testing occurred beforehand to obtain a visual proof of concept. Multiple data points were taken at each designated pressure to ensure consistency. The major conclusions that will come from this paper will be the working back pressures and mass flow rates of the [Emim][EtSO4] and [HAN] monopropellant for the chemical mode of this propulsion system.
Biography
Alex Mundahl is a senior in Aerospace Engineering, and is currently performing undergraduate research for Dr. Rovey in the Aerospace Plasma Laboratory on a Multi-Mode Propulsion system for small spacecraft. He intends on pursuing a Ph.D. with an emphasis in space propulsion while continuing his research. Some of his previous experience includes being the Lead of the Aerodynamics and Propulsion subgroup for the AAVG rocket design team on campus, an active member of the M-SAT team, and a research assistant for the Center of Excellence for Aerospace Particulate Emission Reduction Research.
Research Category
Engineering
Presentation Type
Poster Presentation
Document Type
Poster
Location
Upper Atrium/Hallway
Presentation Date
11 Apr 2016, 1:00 pm - 3:00 pm
Linear Burn Rates of Monopropellants for Multi-Mode Micropropulsion
Upper Atrium/Hallway
A linear strand burner setup was used to obtain linear burn rate characteristics for the mixture of 1-ethyl-3-methylimidazolium ethyl sulfate [Emim][EtSO4] and Hydroxyl Ammonium Nitrate (HAN) . A closed, pressurized system with an Argon atmosphere provided the environment to conductively heat a small cylinder of propellant within a length of quartz tubing through a length of nickel-chromium wire. The initial change and maximum pressure within the system were recorded to calculate the burn time of each test. This process occurred for varying pressures within the range 0-300psig. Open air testing occurred beforehand to obtain a visual proof of concept. Multiple data points were taken at each designated pressure to ensure consistency. The major conclusions that will come from this paper will be the working back pressures and mass flow rates of the [Emim][EtSO4] and [HAN] monopropellant for the chemical mode of this propulsion system.
