Next Article in Journal
Good Code Sets from Complementary Pairs via Discrete Frequency Chips
Previous Article in Journal
Assessment of CFD Capability for Hypersonic Shock Wave Laminar Boundary Layer Interactions
Previous Article in Special Issue
Vortex Lattice Simulations of Attached and Separated Flows around Flapping Wings
Open AccessArticle

Development of Hollow Cathodes for Space Electric Propulsion at Sitael

Space Propulsion Division, Sitael, 56121 Pisa, Italy
Department of Civil and Industrial Engineering, University of Pisa, 56126 Pisa, Italy
Author to whom correspondence should be addressed.
Academic Editor: Konstantinos Kontis
Aerospace 2017, 4(2), 26;
Received: 9 March 2017 / Revised: 26 April 2017 / Accepted: 3 May 2017 / Published: 6 May 2017
(This article belongs to the Special Issue State-of-the-Art Aerospace Sciences and Technologies in Europe)
Hollow cathodes are electron sources used for the gas ionization and the beam neutralization in both ion and Hall effect thrusters (HETs). A reduction of power and propellant consumption from the cathode is particularly needed in small satellite applications, where power and mass budgets are inherently limited. Concurrently, the interest in high-power HETs is increasingly fostered for a number of space applications, including final positioning and station-keeping of Geostationary Earth Orbit (GEO) satellites, spacecraft transfers from Low Earth Orbit (LEO) to GEO, and deep-space exploration missions. As such, several hollow cathodes have been developed and tested at Sitael, each conceived for a specific power class of thrusters. A numerical model was used during the cathode design to define the geometry, in accordance with the thruster unit specifications in terms of discharge current, mass flow rate, and lifetime. Lanthanum hexaboride (LaB6) hollow cathodes were successfully developed for HETs with discharge power ranging from 100 W to 20 kW. Experimental campaigns were carried out in both stand-alone and coupled configurations, to verify the operation of the cathodes and validate the numerical model. The comparison between experimental and theoretical results are presented, offering a sound framework to drive the design of future hollow cathodes. View Full-Text
Keywords: electric propulsion; Hall thrusters; hollow cathodes electric propulsion; Hall thrusters; hollow cathodes
Show Figures

Figure 1

MDPI and ACS Style

Pedrini, D.; Misuri, T.; Paganucci, F.; Andrenucci, M. Development of Hollow Cathodes for Space Electric Propulsion at Sitael. Aerospace 2017, 4, 26.

AMA Style

Pedrini D, Misuri T, Paganucci F, Andrenucci M. Development of Hollow Cathodes for Space Electric Propulsion at Sitael. Aerospace. 2017; 4(2):26.

Chicago/Turabian Style

Pedrini, Daniela; Misuri, Tommaso; Paganucci, Fabrizio; Andrenucci, Mariano. 2017. "Development of Hollow Cathodes for Space Electric Propulsion at Sitael" Aerospace 4, no. 2: 26.

Find Other Styles
Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Article Access Map by Country/Region

Search more from Scilit
Back to TopTop