Hall Thruster Development for Japanese Space Propulsion Programs

Abstract

Three different types of high power Hall thrusters-anode layer type, magnetic layer type with high specific impulse, and magnetic layer type with dual mode operation (high thrust mode and high specific impulse mode)-have been developed, and the thrust performance of each thruster has been evaluated. The thrust of the anode layer type thruster is in the range of 19-219 mN, with power in the range of 325-4500 W. The thrust of the high specific impulse magnetic layer type thruster was 102 mN, with specific impulse of 3300 s. The thrust of the bimodal operation magnetic layer thruster was 385 mN with specific impulse of 1200 s, and 300 mN with specific impulse of 2330 s. The performance of these thrusters demonstrates that the Japanese electric propulsion community has the capability to develop a thruster for commercial use.

Wall Ion Loss Reduction by Acceleration Zone Shifting in Anode-Layer Hall Thruster

“…In Japan, a research project to develop highperformance TAL thruster named "RAIJIN" is in progress. The 4.5-kW class RAIJIN94 attained the thrust efficiency of 0.60, which was comparable with the efficiencies of SPTs of similar input power levels 4) . A 2-kW RAIJIN66 was also designed where the discharge channel and magnetic field geometries were similarly scaled from those of RAIJIN94 so that the discharge plasma properties should be similar 5) .…”

A fast convergence fourth-order Vlasov model for Hall thruster ionization oscillation analyses

“…The Vlasov equation solver is coupled with the magnetized electron fluid model for a HT simulation. The simulation target is the HT developed at The University of Tokyo [27]. An axial 1D1V simulation is performed.…”

Wall Ion Loss Reduction by Acceleration Zone Shifting in Anode-Layer Hall Thruster

“…The optimal design and operation regime for TAL-type Hall thrusters with xenon and alternative propellants have been investigated [4,5]. Hamada et al developed a 5-kW TAL characterized by a magnetic field geometry where the peak of the magnetic flux density is located downstream of the channel exit [6]. This thruster attained a maximum thrust efficiency of 0.60, which is comparable to the efficiencies of SPTs with the same input power level.…”