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Aerothermal design of Crew Escape System.

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Title: Aerothermal design of Crew Escape System.
Authors: Lakshmi, K. S.1 lakshmi_kota@vssc.gov.in, Prabhu, M. Ram1, Padmanabhan, Rishi1, Pandey, Ullekh1, Manirajan, M.2, Anoop, P.1, Sivamurugan, T.3, Sundar, B.1, Chacko, M. J.4
Source: Current Science (00113891). 1/10/2021, Vol. 120 Issue 1, p110-115. 6p.
Subjects: Human space flight, Escapes, Hygrothermoelasticity, Heat flux, Design, Hypersonic aerodynamics
Abstract: Crew safety holds highest priority in manned space missions. Crew Escape System (CES) intends to rescue the Crew Module (CM) which accommodates crew members in case of emergency abort situations. Pad Abort Test (PAT) demonstrates the functioning of CES during abort scenarios at the launch pad. CES pulls away CM from the launch pad using specially designed, quick-acting solid Escape Motors. CES-PAT vehicle is engulfed in hot exhaust plumes of these motors during its ascent, exposing the vehicle surfaces to severe thermal environments. Hence estimation of aerothermal heating levels and Thermal Protection System (TPS) design for CES-PAT vehicle structures are mission-critical. Thermal management of avionic packages housed inside CM is to be ensured for its safe functioning. This article highlights the different aerothermal environments experienced during CESPAT mission, design approaches adopted for estimating heating levels, TPS design and thermal management of avionic systems. Post-flight observations and assessment on aerothermal measurements during CES-PAT mission are also included. Aerothermal measurements confirmed the adequacy of the adopted design approach. [ABSTRACT FROM AUTHOR]
Copyright of Current Science (00113891) is the property of Indian Academy of Sciences and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
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  Data: Aerothermal design of Crew Escape System.
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  Data: <searchLink fieldCode="JN" term="%22Current+Science+%2800113891%29%22">Current Science (00113891)</searchLink>. 1/10/2021, Vol. 120 Issue 1, p110-115. 6p.
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  Data: <searchLink fieldCode="DE" term="%22Human+space+flight%22">Human space flight</searchLink><br /><searchLink fieldCode="DE" term="%22Escapes%22">Escapes</searchLink><br /><searchLink fieldCode="DE" term="%22Hygrothermoelasticity%22">Hygrothermoelasticity</searchLink><br /><searchLink fieldCode="DE" term="%22Heat+flux%22">Heat flux</searchLink><br /><searchLink fieldCode="DE" term="%22Design%22">Design</searchLink><br /><searchLink fieldCode="DE" term="%22Hypersonic+aerodynamics%22">Hypersonic aerodynamics</searchLink>
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  Data: Crew safety holds highest priority in manned space missions. Crew Escape System (CES) intends to rescue the Crew Module (CM) which accommodates crew members in case of emergency abort situations. Pad Abort Test (PAT) demonstrates the functioning of CES during abort scenarios at the launch pad. CES pulls away CM from the launch pad using specially designed, quick-acting solid Escape Motors. CES-PAT vehicle is engulfed in hot exhaust plumes of these motors during its ascent, exposing the vehicle surfaces to severe thermal environments. Hence estimation of aerothermal heating levels and Thermal Protection System (TPS) design for CES-PAT vehicle structures are mission-critical. Thermal management of avionic packages housed inside CM is to be ensured for its safe functioning. This article highlights the different aerothermal environments experienced during CESPAT mission, design approaches adopted for estimating heating levels, TPS design and thermal management of avionic systems. Post-flight observations and assessment on aerothermal measurements during CES-PAT mission are also included. Aerothermal measurements confirmed the adequacy of the adopted design approach. [ABSTRACT FROM AUTHOR]
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  Data: <i>Copyright of Current Science (00113891) is the property of Indian Academy of Sciences and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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      – SubjectFull: Design
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              Text: 1/10/2021
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