Development and characterization of ceramic micro chemical propulsion and combustion systems

Ming Hsun Wu, Richard A. Yetter, Vigor Yang

Research output: Chapter in Book/Report/Conference proceedingConference contribution

9 Citations (Scopus)

Abstract

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.

Original languageEnglish (US)
Title of host publication46th AIAA Aerospace Sciences Meeting and Exhibit
StatePublished - Dec 1 2008
Event46th AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 7 2008Jan 10 2008

Publication series

Name46th AIAA Aerospace Sciences Meeting and Exhibit

Other

Other46th AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/7/081/10/08

Fingerprint

Propulsion
Ignition
Monopropellants
Combustion chambers
Electrodes
Liquids
Electric potential
Propellants
Tapes
Nitrates
Silver
Decomposition
Temperature

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Wu, M. H., Yetter, R. A., & Yang, V. (2008). Development and characterization of ceramic micro chemical propulsion and combustion systems. In 46th AIAA Aerospace Sciences Meeting and Exhibit [2008-0966] (46th AIAA Aerospace Sciences Meeting and Exhibit).
Wu, Ming Hsun ; Yetter, Richard A. ; Yang, Vigor. / Development and characterization of ceramic micro chemical propulsion and combustion systems. 46th AIAA Aerospace Sciences Meeting and Exhibit. 2008. (46th AIAA Aerospace Sciences Meeting and Exhibit).
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Wu, MH, Yetter, RA & Yang, V 2008, Development and characterization of ceramic micro chemical propulsion and combustion systems. in 46th AIAA Aerospace Sciences Meeting and Exhibit., 2008-0966, 46th AIAA Aerospace Sciences Meeting and Exhibit, 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States, 1/7/08.

Development and characterization of ceramic micro chemical propulsion and combustion systems. / Wu, Ming Hsun; Yetter, Richard A.; Yang, Vigor.

46th AIAA Aerospace Sciences Meeting and Exhibit. 2008. 2008-0966 (46th AIAA Aerospace Sciences Meeting and Exhibit).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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N2 - 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.

AB - 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.

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Wu MH, Yetter RA, Yang V. Development and characterization of ceramic micro chemical propulsion and combustion systems. In 46th AIAA Aerospace Sciences Meeting and Exhibit. 2008. 2008-0966. (46th AIAA Aerospace Sciences Meeting and Exhibit).