Evaluations of Silica Aerogel-Based Flexible Blanket as Passive Thermal Control Element for Spacecraft Applications
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Evaluations of Silica Aerogel-Based Flexible Blanket as Passive Thermal Control Element for Spacecraft Applications MohammedAdnan Hasan, S. Rashmi, A.CarmelMary Esther, PrudhiviYashwantkumar Bhavanisankar, BaburaoN. Sherikar, N. Sridhara, and Arjun Dey (Submitted July 12, 2017; in revised form February 8, 2018) The feasibility of utilizing commercially available silica aerogel-based flexible composite blankets as passive thermal control element in applications such as extraterrestrial environments is investigated. Differential scanning calorimetry showed that aerogel blanket was thermally stable over – 150 to 126 °C. The outgassing behavior, e.g., total mass loss, collected volatile condensable materials, water vapor regained and recovered mass loss, was within acceptable range recommended for the space applications. ASTM tension and tear tests confirmed the materialÕs mechanical integrity. The thermo-optical properties remained nearly unaltered in simulated space environmental tests such as relative humidity, thermal cycling and thermo-vacuum tests and confirmed the space worthiness of the aerogel. Aluminized Kapton stitched or anchored to the blanket could be used to control the optical transparency of the aerogel. These outcomes highlight the potential of commercial aerogel composite blankets as passive thermal control element in spacecraft. Structural and chemical characterization of the material was also done using scanning electron microscopy, Fourier transform infrared spectroscopy and x-ray photoelectron spectroscopy. Keywords
aerogel, composite, DSC, mechanical properties, microstructure, outgassing, space environmental tests, thermo-optical properties, XPS
1. Introduction In general, spacecraft normally operate in an extreme environment, experiencing large differences in temperature that ranges from cryogenic to + 150 °C. Therefore, appropriate thermal control systems (TCS), such as multilayer insulation (MLI) blankets, solar reflectors, active/passive cooling and heating systems, are required, along with associated electronic components, to maintain payloads within an acceptable temperature range during all phases of operation (Ref 1, 2). Presently, polyimide- and polyester-based MLI blankets are most common passive thermal control element spread over the outside surface of the spacecraftÕs structure (Ref 1, 2). MLI blanket is one of the best thermal insulating materials while it Mohammed Adnan Hasan, Thermal Systems Group, ISRO Satellite Centre, Vimanapura Post, Bangalore 560017, India; and Department of Ceramic and Cement Technology, Poojya Doddappa Appa (PDA) College of Engineering, Kalaburgi 585102, India; S. Rashmi and Baburao N. Sherikar, Department of Ceramic and Cement Technology, Poojya Doddappa Appa (PDA) College of Engineering, Kalaburgi 585102, India; A.Carmel Mary Esther, N. Sridhara, and Arjun Dey, Thermal Systems Group, ISRO Satellite Centre, Vimanapura Post, Bangalore 560017, India; and Prudhivi Yashwantkumar Bhavanisankar, Thermal Systems Group, ISRO Sa
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