Related references
Note: Only part of the references are listed.
Article
Engineering, Aerospace
J. M. Tejeda et al.
Summary: An investigation on an oxygen-fuelled Hall Effect Thruster was conducted to study the effects of different discharge channel axial lengths, ceramic walls, and anode materials. The study found that a channel length of 13.1 mm performed the best in terms of thrust, specific impulse, and thrust efficiency. The impact of different wall materials and anode materials on the thruster's performance was also analyzed.
Article
Engineering, Aerospace
Alexander Schwertheim et al.
Summary: This study proposes an electric propulsion system that uses water as a propellant for a Hall effect thruster through in situ electrolysis. By supplying the generated oxygen to the thruster anode and the hydrogen to the neutralising cathode, the issue of cathode emitters being poisoned is mitigated. The system benefits from the low cost, high storability, and in situ resource utilisation potential of water, and can also synergize with water electrolysis chemical propulsion systems. The experimental results show that the wall material of the thruster channel has a significant impact on thrust, and increasing the thickness of the magnetic region within the thruster also reduces thrust, specific impulse, and thrust efficiency. The study evaluates the performance of the device under different power and mass flow conditions, and finds that the best performance is achieved with the shallowest channel depth, with the highest thrust, specific impulse, and anode thrust efficiency obtained at the lowest mass flow.
Article
Engineering, Aerospace
J. M. Tejeda et al.
Summary: This study proposes using radiofrequency excitation in single-stage Hall Effect Thrusters to improve their performance. The reliability of a 2D axial-radial plasma simulation software called PlasmaSim is verified and validated against experimental measurements. The impact of radiofrequency excitation on thruster performance and in-channel plasma properties is analyzed and quantified.
Article
Engineering, Aerospace
Takahito Motoki et al.
Summary: This study experimentally examined the importance of magnetic field topology for the miniature microwave discharge cathode driven by water in realizing water ion thrusters. It was found that the magnetic field topology with the magnetic field lines passing through the orifice hole without intersecting the cathode increased the electron emission current. The dependency of electron emission current on the magnetic field topology decreased with decreasing mass flow rate or microwave power, and varied significantly with different magnetic field topologies for the electron emission current dependency on mass flow rate.
Article
Engineering, Aerospace
Alexander Schwertheim et al.
Summary: This study proposes modifying a Hall effect thruster to operate on the products of water electrolysis, utilizing the low cost and high storability of water. Experimental results showed that thrust, specific impulse, and thrust efficiency all increase linearly with power within a certain range. Changing the mass flow rate had little impact on thrust efficiency.
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Summary: Imperial College London and the European Space Agency have developed a hanging pendulum thrust balance for characterizing static fire electric propulsion and chemical micro-propulsion devices with thrust in the range of 1 mN to 1 N. The device uses stainless steel flexures to suspend a pendulum platform, with displacement measured using an optical laser triangulation sensor. Thermal stability is ensured by a closed-loop self-compensating heating system.
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