Dr Moe Ahmed
About
My research project
Investigation of External Discharge in plasma thrusters for Space Propulsion ApplicationsUsing a combination of experiments and simulations, this project will complete research on a novel technology for an electrically powered plasma thruster by delivering large thrust density without the need to expose electrodes to plasma, aiming at achieving longer lifetime, lower system complexity, and flexibility in terms of suitable propellants in comparison with existing flying technology. Over coming Electrode erosion and lifetime limiting factors by implementing an External Discharge system with novel-innovative neutraliser technologies, Innovative external discharge concepts have been implemented to improve lifetime and efficiency issues by moving the discharge external to the channel. Electric propulsion is supporting the new space economy by fulfilling mission requirements as primary propulsion units, giving access to both lower and higher orbits as well as longer useful mission lifetimes for interplanetary travel and deep space exploration.
The experimental investigation addresses scientific and commercial needs by developing novel and innovative neutralisers to assist with testing of a alternative low power long lifetime cost-effective Hall thruster, the External Plasma Discharge Hall Thruster (XPT) operated with legacy and alternative propellants.
Supervisors
Using a combination of experiments and simulations, this project will complete research on a novel technology for an electrically powered plasma thruster by delivering large thrust density without the need to expose electrodes to plasma, aiming at achieving longer lifetime, lower system complexity, and flexibility in terms of suitable propellants in comparison with existing flying technology. Over coming Electrode erosion and lifetime limiting factors by implementing an External Discharge system with novel-innovative neutraliser technologies, Innovative external discharge concepts have been implemented to improve lifetime and efficiency issues by moving the discharge external to the channel. Electric propulsion is supporting the new space economy by fulfilling mission requirements as primary propulsion units, giving access to both lower and higher orbits as well as longer useful mission lifetimes for interplanetary travel and deep space exploration.
The experimental investigation addresses scientific and commercial needs by developing novel and innovative neutralisers to assist with testing of a alternative low power long lifetime cost-effective Hall thruster, the External Plasma Discharge Hall Thruster (XPT) operated with legacy and alternative propellants.
Affiliations and memberships
ResearchResearch interests
Plasma Propulsion, Plasma Diagnostics, Hollow Cathodes, Plasma thrusters Neutralisers, Electrostatics Propulsion systems
Research interests
Plasma Propulsion, Plasma Diagnostics, Hollow Cathodes, Plasma thrusters Neutralisers, Electrostatics Propulsion systems
Publications
A hollow cathode with a modular design has been developed to assist with laboratory testing of plasma-based thrusters for satellite applications. This novel modular design includes interchangeable components for varying the geometry and tailoring the configuration to specific applications, as well as easing the replacement of individual components in the case of damage. The modular hollow cathode also presents unconventional design features aimed at improving the heating efficiency: the heater is in direct contact with the emitter and the keeper is not in physical contact with the cathode base. The modular hollow cathode development has been based on a combination of theoretical modelling and experimental testing. The influence of the novel mechanical assembly has been investigated by characterising the operational envelope at different propellant mass flow rates for xenon and krypton. The modular hollow cathode has demonstrated stable operation by sustaining discharge currents between 0.5 and 4 A at different conditions. Finally, the cathode has been coupled with a Hall-type plasma thruster operating in the 0.3–2.5 A anode current range. This paper outlines development, experimental validation of this peculiar mechanical cathode configuration, covering plasma and thermal modelling, standalone testing, and coupled Hall-type thruster operation.