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Effect of Resistive and Plasma Heating on the Specific Impulse of a Ceramic Cold Gas Thruster
Försvarshögskolan, Militärvetenskapliga institutionen (MVI), Avdelningen för ledningsvetenskap och militärteknik (ALM), Sektionen för militärtekniska system (MteS).ORCID-id: 0000-0002-0501-0887
Uppsala Universitet. (Ångström Space Technology Centre)
Uppsala University. (Division of Microsystems)
Uppsala University. (Ångström Space Technology Centre)
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2019 (Engelska)Ingår i: Journal of microelectromechanical systems, ISSN 1057-7157, E-ISSN 1941-0158, Vol. 28, nr 2, s. 235-244Artikel i tidskrift (Refereegranskat) Published
Abstract [en]

Research and development of small satellites has continued to expand over the last decades. However, propulsion systems with adequate performance have persisted to be a great challenge. In this paper, the effects of three different heaters on the specific impulse and overall thrust efficiency of a cold gas microthruster are presented. They consisted of a conventional, printed resistive thick-film element, a freely suspended wire, and a stripline split-ring resonator microplasma source and were integrated in a single device made from high-temperature co-fired ceramics (HTCC). The devices were evaluated in two setups, where the first measured thrust and the other shock cell geometry. In addition, the resistive elements were evaluated as gas temperature sensors. The microplasma source was found to provide the greatest improvement in both specific impulse and thrust efficiency, increasing the former from an un- heated level of 44 s to 55 s when heating with a power of 1.1 W. This corresponded to a thrust efficiency of 53 %. This could be compared to the results from the wire and printed heaters which were 50 s and 18 %, and 45 s and 14 %, respectively. The combined results also showed that imaging the shock cells of a plasma heated thruster was a simple and effective way to determine its performance compared to the traditional thrust balance method.

Ort, förlag, år, upplaga, sidor
2019. Vol. 28, nr 2, s. 235-244
Nyckelord [en]
microthruster, HTCC, resistive heating, plasma heating, specific impulse, shock cells
Nationell ämneskategori
Rymd- och flygteknik
Forskningsämne
Försvarssystem
Identifikatorer
URN: urn:nbn:se:fhs:diva-8166DOI: 10.1109/JMEMS.2019.2893359OAI: oai:DiVA.org:fhs-8166DiVA, id: diva2:1248889
Tillgänglig från: 2018-09-17 Skapad: 2018-09-17 Senast uppdaterad: 2019-09-04Bibliografiskt granskad
Ingår i avhandling
1. Sense, Actuate and Survive: Ceramic Microsystems for High-Temperature Aerospace Applications
Öppna denna publikation i ny flik eller fönster >>Sense, Actuate and Survive: Ceramic Microsystems for High-Temperature Aerospace Applications
2018 (Engelska)Doktorsavhandling, sammanläggning (Övrigt vetenskapligt)
Abstract [en]

In aerospace applications, but also in manufacturing, mining, energy industry and natural hazards, high temperature, corrosion, erosion and radiation, challenge the performance and being of hardware.

In this work, high-temperature co-fired ceramic (HTCC) alumina and platinum have been used for a range of devices intended for aerospace applications at up to 1000°C.

The thermomechanics of a pressure sensor was investigated, and the interfacing was attained by wireless powering and reading. However, read range was limited and sensitivity decreased with temperature. Silver, electroplated after sintering, was found to remedy this until it eventually alloyed with platinum.

Copper was electroplated and oxidized for oxygen storage in a microcombustor, intended for sample preparation for optogalvanic spectroscopy (OGS) to indicate extraterrestrial life. Despite delamination, caused by residual stresses, the device operated successfully.

Conversely, pre-firing metallization by integration of platinum wires was studied. Freely suspended, and despite heat-induced shape irregularities, these were found advantageous over screen printed elements for gas heating, and temperature and pressure sensing. By fusing off the wires, spherical tips, allowing for impedance monitoring of microplasma sources in, e.g., OGS, were formed.

Microplasma sources can also be used for gas heating. This, together with screen printed and suspended resistive heaters, was evaluated in a microthruster, showing that plasma heating is the most effective, implying fuel consumption reduction in satellite propulsion.

In conclusion, HTCC alumina microdevices are thermally stable and could benefit several aerospace applications, especially with the complementary metallization schemes devised here.

Future developments are expected to include both processing and design, all with the intention of sensing, actuating and surviving in high-temperature environments.

Ort, förlag, år, upplaga, sidor
Uppsala: Acta Universitatis Upsaliensis, 2018. s. 44
Serie
Digital Comprehensive Summaries of Uppsala Dissertations from the Faculty of Science and Technology, ISSN 1651-6214 ; 1696
Nyckelord
high temperature, ceramics, microsystems, aerospace, sensors, thrusters
Nationell ämneskategori
Rymd- och flygteknik Materialteknik
Forskningsämne
Försvarssystem
Identifikatorer
urn:nbn:se:fhs:diva-8743 (URN)978-91-513-0392-5 (ISBN)
Disputation
2018-09-21, Polhemsalen, Ångströmlaboratoriet, Lägerhyddsvägen 1, 09:30 (Svenska)
Opponent
Handledare
Tillgänglig från: 2019-09-04 Skapad: 2019-09-04 Senast uppdaterad: 2019-09-04Bibliografiskt granskad

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