Development and characterization of ceramic micro chemical propulsion and combustion systems

Ming Hsun Wu, Richard A. Yetter, Vigor Yang

研究成果: Conference contribution

12 引文 斯高帕斯(Scopus)

摘要

This paper reports on the development of a liquid monopropellant microthruster utilizing electrolytic ignition. Low temperature co-fired ceramic tape technology was used to fabricate the microthrusters. The microthrusters had integrated silver electrodes to enable ignition of hydroxylammonium nitrate based liquid monopropellants by electrolytic decomposition. The volume of the thruster combustion chamber was 0.82 mm3. The microthruster was successfully ignited, and a thrust output of approximately 200 mN was measured with a voltage input of 45 V. Energy input as small as 1.9 J was achieved for ignition, and ignition delay as short as 224.5 ms was recorded. Ignition delays were found dependent on the type of HAN-based propellant, the voltage potential, and the size of the electrodes within the combustion chamber. When ignition was rapid, some cracking of the thruster body was observed.

原文English
主出版物標題46th AIAA Aerospace Sciences Meeting and Exhibit
發行者American Institute of Aeronautics and Astronautics Inc.
ISBN(列印)9781563479373
DOIs
出版狀態Published - 2008

出版系列

名字46th AIAA Aerospace Sciences Meeting and Exhibit

All Science Journal Classification (ASJC) codes

  • 航空工程

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