Title

Linear Burn Rates of Monopropellants for Multi-Mode Micropropulsion

Presenter Information

Alex Mundahl

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

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Apr 11th, 1:00 PM Apr 11th, 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.