Actions for Propulsion System Development for the Iodine Satellite (iSAT) Demonstration Mission

Email RIS file
Bookmark
Report an Issue

Propulsion System Development for the Iodine Satellite (iSAT) Demonstration Mission

Author
Szabo, James
Published
July 6, 2015.
Physical Description
1 electronic document
Additional Creators
Lee, Lauren, Hickman, Tyler A., Kamhawi, Hani, Seixal, Joao F., Jerman, Gregory A., Pote, Bruce, Mauro, Stephanie L., Dankanich, John, Calvert, Derek H., Peeples, Stephen R., Lewis, Brandon L., and Polzin, Kurt A.
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The development and testing of a 200-W iodine-fed Hall thruster propulsion system that will be flown on a 12-U CubeSat is described. The switch in propellant from more traditional xenon gas to solid iodine yields the advantage of high density, low pressure propellant storage but introduces new requirements that must be addressed in the design and operation of the propulsion system. The thruster materials have been modified from a previously-flown xenon Hall thruster to make it compatible with iodine vapor. The cathode incorporated into this design additionally requires little or no heating to initiate the discharge, reducing the power needed to start the thruster. The feed system produces iodine vapor in the propellant reservoir through sublimation and then controls the flow to the anode and cathode of the thruster using a pair of proportional flow control valves. The propellant feeding process is controlled by the power processing unit, with feedback control on the anode flow rate provided through a measure of the thruster discharge current. Thermal modeling indicates that it may be difficult to sufficiently heat the iodine if it loses contact with the propellant reservoir walls, serving to motivate future testing of that scenario to verify the modeling result and develop potential mitigation strategies. Preliminary, short-duration materials testing has thus-far indicated that several materials may be acceptable for prolonged contact with iodine vapor, motivating longer-duration testing. A propellant loading procedure is presented that aims to minimize the contaminants in the feed system and propellant reservoir. Finally, an 80-hour duration test being performed to gain experience operating the thruster over long durations and multiple restarts is discussed.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20150016536.
IEPC-2015-09.
M15-4731.
ISTS-2015-b-09.
International Electric Propulsion Conference (IEPC) ; 6-10 Jul. 2015; Kobe-Hyogo; Japan.
International Symposium on Space Technology and Sciences (ISTS); 6-10 Jul. 2015; Kobe-Hyogo; Japan.
Nano-Satellite Symposium (NSAT); 6-10 Jul. 2015; Kobe-Hyogo; Japan.
Terms of Use and Reproduction
Copyright, Distribution as joint owner in the copyright.
View MARC record | catkey: 17531767