Performance of transpiration cooled heat shields for re-entry vehicles
This paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient te...
| Main Authors: | , , |
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| Format: | Journal article |
| Language: | English |
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American Institute of Aeronautics and Astronautics
2019
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| _version_ | 1797102300829843456 |
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| author | Hermann, T McGilvray, M Naved, I |
| author_facet | Hermann, T McGilvray, M Naved, I |
| author_sort | Hermann, T |
| collection | OXFORD |
| description | This paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient temperature of a transpiration cooled heat shield. The performance of transpiration cooling is assessed by calculating the overall required coolant mass for different steady state and transient flight scenarios. Spatially and temporally optimised mass injection is presented for various flight conditions. The majority of the injection is required on the spherical nose segment of the blunted cone. Carbon/Carbon composite ceramic and the ultra high temperature ceramic Zirconium diboride are considered as wall materials. Both materials require similar amounts of coolant injection. In continuous hypersonic cruise, transpiration cooling is highly effective for flight conditions with velocities below 8 km s−1 and altitudes above 40 km. For transient re-entry, transpiration cooling is most viable for trajectories of entry velocities below 8.5 km s−1 and ballistic coefficients below 2.1 kg m−2. |
| first_indexed | 2024-03-07T06:04:01Z |
| format | Journal article |
| id | oxford-uuid:ed382e8e-855f-48b7-b995-3b3571c723a8 |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-07T06:04:01Z |
| publishDate | 2019 |
| publisher | American Institute of Aeronautics and Astronautics |
| record_format | dspace |
| spelling | oxford-uuid:ed382e8e-855f-48b7-b995-3b3571c723a82022-03-27T11:23:15ZPerformance of transpiration cooled heat shields for re-entry vehiclesJournal articlehttp://purl.org/coar/resource_type/c_dcae04bcuuid:ed382e8e-855f-48b7-b995-3b3571c723a8EnglishSymplectic Elements at OxfordAmerican Institute of Aeronautics and Astronautics2019Hermann, TMcGilvray, MNaved, IThis paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient temperature of a transpiration cooled heat shield. The performance of transpiration cooling is assessed by calculating the overall required coolant mass for different steady state and transient flight scenarios. Spatially and temporally optimised mass injection is presented for various flight conditions. The majority of the injection is required on the spherical nose segment of the blunted cone. Carbon/Carbon composite ceramic and the ultra high temperature ceramic Zirconium diboride are considered as wall materials. Both materials require similar amounts of coolant injection. In continuous hypersonic cruise, transpiration cooling is highly effective for flight conditions with velocities below 8 km s−1 and altitudes above 40 km. For transient re-entry, transpiration cooling is most viable for trajectories of entry velocities below 8.5 km s−1 and ballistic coefficients below 2.1 kg m−2. |
| spellingShingle | Hermann, T McGilvray, M Naved, I Performance of transpiration cooled heat shields for re-entry vehicles |
| title | Performance of transpiration cooled heat shields for re-entry vehicles |
| title_full | Performance of transpiration cooled heat shields for re-entry vehicles |
| title_fullStr | Performance of transpiration cooled heat shields for re-entry vehicles |
| title_full_unstemmed | Performance of transpiration cooled heat shields for re-entry vehicles |
| title_short | Performance of transpiration cooled heat shields for re-entry vehicles |
| title_sort | performance of transpiration cooled heat shields for re entry vehicles |
| work_keys_str_mv | AT hermannt performanceoftranspirationcooledheatshieldsforreentryvehicles AT mcgilvraym performanceoftranspirationcooledheatshieldsforreentryvehicles AT navedi performanceoftranspirationcooledheatshieldsforreentryvehicles |