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Surfaces with high solar reflectance and high thermal emittance on structured silicon for spacecraft thermal control
Uppsala universitet, Teknisk-naturvetenskapliga vetenskapsområdet, Tekniska sektionen, Institutionen för teknikvetenskaper, Elektricitetslära och åskforskning.
Uppsala universitet, Teknisk-naturvetenskapliga vetenskapsområdet, Tekniska sektionen, Institutionen för teknikvetenskaper, Mikrostrukturteknik.
Uppsala universitet, Teknisk-naturvetenskapliga vetenskapsområdet, Tekniska sektionen, Institutionen för teknikvetenskaper, Fasta tillståndets fysik.
Uppsala universitet, Teknisk-naturvetenskapliga vetenskapsområdet, Tekniska sektionen, Institutionen för teknikvetenskaper, Elektricitetslära och åskforskning.
Vise andre og tillknytning
2008 (engelsk)Inngår i: Optical materials (Amsterdam), ISSN 0925-3467, E-ISSN 1873-1252, Vol. 30, nr 9, s. 1410-1421Artikkel i tidsskrift (Fagfellevurdert) Published
Abstract [en]

Presented here is an examination of unstructured and structured (by anisotropic etching), monocrystalline silicon wafers coated with sputter deposited aluminum and chemical vapor deposited silicon dioxide for high solar reflectance and high thermal emittance, respectively. The topography of the samples was characterized with optical and scanning electron microscopy. Optical properties were examined with reflectance and transmittance spectroscopy, partly by usage of an integrating sphere. The measurement results were used to estimate the equilibrium temperature of the surfaces in space. The suitability of the surfaces with high solar reflectance and high thermal emittance to aid in the thermal control of miniaturized, highly integrated components for space applications is discussed. A silicon dioxide layer on a metal layer results in a slightly lower reflectance when compared to surfaces with only a metal layer, but might be beneficial for miniaturized space components and modules that have to dissipate internally generated heat into open space. Additionally, it is an advantage to microstructure the emitting surface for enhanced radiation of excess heat.

sted, utgiver, år, opplag, sider
2008. Vol. 30, nr 9, s. 1410-1421
Emneord [en]
solar reflectance, thermal emittance, energy transfer, coatings, thermo-optical materials, satellite thermal control
HSV kategori
Identifikatorer
URN: urn:nbn:se:uu:diva-14767DOI: 10.1016/j.optmat.2007.08.005ISI: 000256413100012OAI: oai:DiVA.org:uu-14767DiVA, id: diva2:42538
Tilgjengelig fra: 2008-05-05 Laget: 2008-05-05 Sist oppdatert: 2017-12-11bibliografisk kontrollert
Inngår i avhandling
1. Integrated Communications and Thermal Management Systems for Microsystem-based Spacecraft: A Multifunctional Microsystem Approach
Åpne denne publikasjonen i ny fane eller vindu >>Integrated Communications and Thermal Management Systems for Microsystem-based Spacecraft: A Multifunctional Microsystem Approach
2006 (engelsk)Doktoravhandling, med artikler (Annet vitenskapelig)
Abstract [en]

This thesis explores the potential of multifunctional silicon-based microsystems for advanced integrated nanospacecraft (AIN). Especially, multifunctional microsystems with the coexistant functions of communications and thermal management implemented in multilayer silicon stacks are approached with systems study. Host vehicles, composed of microsystems, including micro/nano-spacecraft and spherical rovers are contemplated with respect to future performance and implications, system level design, and breadboard realizations. A module of great importance, named the "integrated communications and thermal management system for advanced integrated spacecraft" or ICTM, symbolizes the achievements within the field of self-contained microsystems and is a prioritized entity throughout the thesis. The ICTM is natively placable onboard all types of highly miniaturized craft.

The single AIN spacecraft and future clusters of these are investigated with respect to future full scale implementation of space systems designed and implemented with the distributed reconfigurable nanospacecraft cluster (DRNC) concept. Here, a true entanglement of microsystems technology (MST) and miniaturized spacecraft technology can revolutionize the applications, cost, and span of conceivable space missions.

An intended communications scenario supporting a data rate of 1 Mbps, for the transmitter, is achieved during 6 minutes with a maximum continuous power dissipation of 10 W. Thermal simulations support the expectation, of a thermally biased ICTM, that the module is capable of supporting this energy burst, by using the mechanisms of heat storage and heat switches, and still fulfilling the requirements imposed by AIN type of spacecraft. In addition, multiple functional surfaces for the ICTM are evaluated with respect to equilibrium temperature and process compatibility. The tailored surfaces provide temperature control using micromachining methods.

A design of a micromachined Ka-band front end with several MST enabled features is presented including e.g. vias, phase-shifters, and antennas. Similar antennas have been manufactured resulting in an evaluation of ring- and slot-antennas on silicon substrate. Based on a primitive version of the ICTM, a S-band patch antenna has been successfully implemented and characterized. Included in the thesis is a microthruster, an enabling technology for DRNC.

sted, utgiver, år, opplag, sider
Uppsala: Acta Universitatis Upsaliensis, 2006. s. 45
Serie
Digital Comprehensive Summaries of Uppsala Dissertations from the Faculty of Science and Technology, ISSN 1651-6214 ; 141
Emneord
Electronics, nanospacecraft, MST, MEMS, silicon, communication, thermal management, antenna, paraffin, PCM, multifunctional, microsystems, Elektronik
HSV kategori
Identifikatorer
urn:nbn:se:uu:diva-6316 (URN)91-554-6449-1 (ISBN)
Disputas
2006-02-10, Häggsalen, Ångströmlaboratoriet, Lägerhyddsvägen 1, Uppsala, 13:15
Opponent
Veileder
Tilgjengelig fra: 2006-01-19 Laget: 2006-01-19 Sist oppdatert: 2013-09-20bibliografisk kontrollert
2. Copper indium gallium diselenide sun angle detectors and MEMS thermal control surfaces for space applications
Åpne denne publikasjonen i ny fane eller vindu >>Copper indium gallium diselenide sun angle detectors and MEMS thermal control surfaces for space applications
2008 (engelsk)Licentiatavhandling, med artikler (Annet vitenskapelig)
sted, utgiver, år, opplag, sider
Uppsala: Uppsala University, Department of Engineering Sciences, 2008. s. 102
HSV kategori
Forskningsprogram
Teknisk fysik med inriktning mot elektronik
Identifikatorer
urn:nbn:se:uu:diva-286396 (URN)
Presentation
2008-05-16, Polhemsalen, 14:13 (engelsk)
Tilgjengelig fra: 2016-04-21 Laget: 2016-04-20 Sist oppdatert: 2016-04-21bibliografisk kontrollert

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