MEMS thruster system for cubesat orbital maneuver applications

Adam Huang, Eui Hyeok Yang

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Scopus citations

Abstract

This paper reviews the previously developed attitude control micro-thruster propulsion unit (The Aerospace Corporation) and a high pressure piezoelectric microvalve (Jet Propulsion Laboratory), and follows up with a conceptual development effort that is currently underway to optimize the benefits of merging these two technologies. The goal is to provide orbital maneuver capabilities for future Air Force and NASA nano/pico-satellite missions, such as inspector satellites for post launch diagnostics, sparse array antennas, field measurements of space weather events, and the calibration of atmospheric drag in the thermosphère. The piezoelectric microvalve developed is capable of low power (3mW), high speed (> 1kHz), and high pressure (70 bar absolute). The target warm gas Newton level propulsion system dry mass is 200 grams and with a volume of < 100 cm3 and the intended first mission is to provide CubeSats the ability to operate at orbits of choice rather than opportunity.

Original languageEnglish
Title of host publicationProceedings of the ASME International Mechanical Engineering Congress and Exposition 2009, IMECE 2009
Pages931-936
Number of pages6
EditionPART B
DOIs
StatePublished - 2010
EventASME 2009 International Mechanical Engineering Congress and Exposition, IMECE2009 - Lake Buena Vista, FL, United States
Duration: 13 Nov 200919 Nov 2009

Publication series

NameASME International Mechanical Engineering Congress and Exposition, Proceedings
NumberPART B
Volume12

Conference

ConferenceASME 2009 International Mechanical Engineering Congress and Exposition, IMECE2009
Country/TerritoryUnited States
CityLake Buena Vista, FL
Period13/11/0919/11/09

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