Journal article
Performance of transpiration cooled heat shields for re-entry vehicles
- Abstract:
- 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.
- Publication status:
- Published
- Peer review status:
- Peer reviewed
Actions
Access Document
- Files:
-
-
(Preview, Accepted manuscript, 17.9KB, Terms of use)
-
(Preview, Accepted manuscript, pdf, 8.8MB, Terms of use)
-
- Publisher copy:
- 10.2514/1.J058515
Authors
- Publisher:
- American Institute of Aeronautics and Astronautics
- Journal:
- AIAA Journal More from this journal
- Volume:
- 58
- Issue:
- 2
- Pages:
- 830-841
- Publication date:
- 2019-12-17
- Acceptance date:
- 2019-10-23
- DOI:
- EISSN:
-
1533-385X
- ISSN:
-
0001-1452
- Language:
-
English
- Keywords:
- Pubs id:
-
pubs:1069067
- UUID:
-
uuid:ed382e8e-855f-48b7-b995-3b3571c723a8
- Local pid:
-
pubs:1069067
- Source identifiers:
-
1069067
- Deposit date:
-
2019-11-01
Terms of use
- Copyright holder:
- Hermann et al.
- Copyright date:
- 2019
- Rights statement:
- © 2019 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
- Notes:
-
This is the accepted manuscript version of the article. The final version is available online from American Institute of Aeronautics and Astronautics at: https://doi.org/10.2514/1.J058515
A correction to this article is available online at: https://doi.org/10.2514/1.J058515.c1
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