Please use this identifier to cite or link to this item:
Title: Passive thermal control design methods, analysis, comparison, and evaluation for micro and nanosatellites carrying infrared imager
Authors: Selvadurai, Shanmugasundaram
Chandran, Amal
Valentini, David
Lamprecht, Bret
Keywords: Engineering::Electrical and electronic engineering
Issue Date: 2022
Source: Selvadurai, S., Chandran, A., Valentini, D. & Lamprecht, B. (2022). Passive thermal control design methods, analysis, comparison, and evaluation for micro and nanosatellites carrying infrared imager. Applied Sciences, 12(6), 2858-.
Journal: Applied Sciences 
Abstract: Advancements in satellite technologies are increasing the power density of electronics and payloads. When the power consumption increases within a limited volume, waste heat generation also increases and this necessitates a proper and efficient thermal management system. Mostly, micro and nanosatellites use passive thermal control methods because of the low cost, no additional power requirement, ease of implementation, and better thermal performance. Passive methods lack the ability to meet certain thermal requirements on larger and smaller satellite platforms. This work numerically studies the performance of some of the passive thermal control techniques such as thermal straps, surface coatings, multi-layer insulation (MLI), and radiators for a 6U small satellite configuration carrying a mid-wave infrared (MWIR) payload whose temperature needs to be cooled down to 100K. Infrared (IR) imagers require low temperature, and the level of cooling is entirely dependent on the infrared wavelengths. These instruments are used for various applications includ-ing Earth observations, defence, and imaging at IR wavelengths. To achieve these low temperatures on such instruments, a micro-cryocooler is considered in this study. Most of the higher heat dissi-pating elements in the satellite are mounted to a heat exchanger plate, which is thermally coupled to an external radiator using thermal straps and heat pipes. The effects of the radiator size, orbital inclinations, space environments, satellite attitude with respect to the sun, and surface coatings are discussed elaborately for a 6U satellite configuration.
ISSN: 2076-3417
DOI: 10.3390/app12062858
Schools: School of Electrical and Electronic Engineering 
Research Centres: Satellite Research Centre 
Rights: © 2022 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https:// 4.0/).
Fulltext Permission: open
Fulltext Availability: With Fulltext
Appears in Collections:EEE Journal Articles

Files in This Item:
File Description SizeFormat 
applsci-12-02858.pdf9 MBAdobe PDFThumbnail

Citations 50

Updated on Sep 17, 2023

Web of ScienceTM
Citations 50

Updated on Sep 14, 2023

Page view(s)

Updated on Sep 19, 2023


Updated on Sep 19, 2023

Google ScholarTM




Items in DR-NTU are protected by copyright, with all rights reserved, unless otherwise indicated.