Research Website
https://engineering.purdue.edu/APSL/
Keywords
Hall Thruster, Electric Propulsion, T-100-3, Plasma, Krypton, Xenon, Ion Flux, Plume, Thrust
Presentation Type
Poster
Research Abstract
Stationary Hall thrusters are electric, moderate-specific impulse propulsion systems developed in Russia. These devices manipulate electric and magnetic fields to expel ionized gas (plasma) components, resulting in thrust. The success of Hall-effect engines in USSR satellite-transfer missions quickly sparked western interest in the design. Extensive government and academic study commenced shortly after the dissolution of the Soviet Union, when the technology was made available to the United States. The common SPT-100 model was the primary subject of such studies. Unfortunately, limited literature exists for rare and uncommon Hall thruster models. The T-100-3 stationary plasma thruster suffers from this gap; few xenon-propellant datasets are readily available. No exhaustive studies have been published with inexpensive and alternative krypton propellant. Our evaluation seeks to comprehensively record and analyze the performance parameters of a krypton-fed T-100-3 stationary plasma thruster. In particular, the discharge voltage, discharge current, erosion, temperature, thrust, efficiency, and specific impulse were investigated with thermocouples and force-calibrated inverse pendulums. Plume distributions and ion flux were additionally measured, using Langmuir probes and Faraday cups. These variables were analyzed over 2.5 approximate hours of run-time with a large range of flow, magnetic, and power operating conditions. Based on a -47% nominal flow state (25.0 sccm anode flow, 10.0 sccm cathode flow, 8.5 W magnetic field, 1.39 kW discharge supply), the T-100-3 achieved thrust values of 28.1 mN with a corresponding specific impulse of 1313.4 s. Our study suggests the feasibility of krypton in moderate-specific impulse satellite keeping missions.
Session Track
Combustion and Energy
Recommended Citation
Adam Patel, Javier Cortina Fernandez, Justin Chow, Osvaldo Alejandro Martin, and Alexey Shashurin,
"Experimental Evaluation of a Krypton Propellant Arrangement in a T-100-3 Hall-Effect Thruster"
(August 2, 2018).
The Summer Undergraduate Research Fellowship (SURF) Symposium.
Paper 40.
https://docs.lib.purdue.edu/surf/2018/Presentations/40
Included in
Electrical and Electronics Commons, Electromagnetics and Photonics Commons, Propulsion and Power Commons, Space Vehicles Commons
Experimental Evaluation of a Krypton Propellant Arrangement in a T-100-3 Hall-Effect Thruster
Stationary Hall thrusters are electric, moderate-specific impulse propulsion systems developed in Russia. These devices manipulate electric and magnetic fields to expel ionized gas (plasma) components, resulting in thrust. The success of Hall-effect engines in USSR satellite-transfer missions quickly sparked western interest in the design. Extensive government and academic study commenced shortly after the dissolution of the Soviet Union, when the technology was made available to the United States. The common SPT-100 model was the primary subject of such studies. Unfortunately, limited literature exists for rare and uncommon Hall thruster models. The T-100-3 stationary plasma thruster suffers from this gap; few xenon-propellant datasets are readily available. No exhaustive studies have been published with inexpensive and alternative krypton propellant. Our evaluation seeks to comprehensively record and analyze the performance parameters of a krypton-fed T-100-3 stationary plasma thruster. In particular, the discharge voltage, discharge current, erosion, temperature, thrust, efficiency, and specific impulse were investigated with thermocouples and force-calibrated inverse pendulums. Plume distributions and ion flux were additionally measured, using Langmuir probes and Faraday cups. These variables were analyzed over 2.5 approximate hours of run-time with a large range of flow, magnetic, and power operating conditions. Based on a -47% nominal flow state (25.0 sccm anode flow, 10.0 sccm cathode flow, 8.5 W magnetic field, 1.39 kW discharge supply), the T-100-3 achieved thrust values of 28.1 mN with a corresponding specific impulse of 1313.4 s. Our study suggests the feasibility of krypton in moderate-specific impulse satellite keeping missions.
https://docs.lib.purdue.edu/surf/2018/Presentations/40