Title :
A micro pulsed plasma thruster (PPT) for the “Dawgstar” spacecraft
Author :
Cassady, R. Joseph ; Hoskins, W. Andrew ; Campbell, Mark ; Rayburn, C.
Author_Institution :
Primex Aerosp. Co., Redmond, WA, USA
Abstract :
The AFOSR/DARPA University Nanosat program aims to produce a small fleet of nanosatellites. Among the most ambitious is the “Dawgstar” from the University of Washington. It proposes to use micro-PPTs to formation fly with two other student-built satellites in a constellation known as ION-F. Dawgstar, planned for launch in 2001, provides a useful technology testbed for future micro- and nano-sat efforts. PPTs were selected because they lend themselves well to very small satellites due to their solid-state nature. The PPT also offers a very high specific impulse compared to other candidate microthrusters. The fundamentals of the PPT propulsion system are described and a preliminary layout of the concept is explained. Preliminary tests results from scaled configurations are presented. A key area for miniaturization is the onboard electronics. The paper describes work underway to miniaturize the PPT electronics to a size consistent with the nanosatellite goals, including design analyses and preliminary testing of electronics breadboards
Keywords :
aerospace propulsion; artificial satellites; electric propulsion; plasma devices; Dawgstar spacecraft; ION-F constellation; formation flying; micro pulsed plasma thruster; miniaturization; nanosatellites; onboard electronics; propulsion system; scaled configurations; solid propellant; technology testbed; Capacitors; Electronic equipment testing; Feeds; Plasmas; Power system reliability; Propulsion; Satellites; Solids; Space vehicles; Voltage;
Conference_Titel :
Aerospace Conference Proceedings, 2000 IEEE
Conference_Location :
Big Sky, MT
Print_ISBN :
0-7803-5846-5
DOI :
10.1109/AERO.2000.878359
