Refine your search
Collections
Co-Authors
Journals
Year
A B C D E F G H I J K L M N O P Q R S T U V W X Y Z All
Packirisamy, S.
- Ceramic Coating on Flexible External Insulation Blankets for Reusable Missions
Abstract Views :230 |
PDF Views:89
Authors
Affiliations
1 Ceramic Matrix Products Division, Analytical Spectroscopy and Ceramics Group, PCM Entity, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
1 Ceramic Matrix Products Division, Analytical Spectroscopy and Ceramics Group, PCM Entity, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 114, No 01 (2018), Pagination: 137-143Abstract
Flexible thermal protection material (flexible external insulation; FEI) is used in the Reusable Launch Vehicle-Technology Demonstrator (RLV-TD) leeward region where multiple curvatures are present. FEI configuration has silica cloth layers on either side with Cerablanket felt sandwiched and stitched together using quartz thread. FEI should ensure an airframe skin temperature in the leeward region within the temperature constraint limits (100°C) of aluminum alloy during the RLV-TD ascent (4.8 W/cm2) and descent (3.7 W/cm2) phases. A ceramic room-temperature coating with low surface solar absorptivity (α) and high thermal emissivity (ε) to generate the required thermal gradient at the backwall was developed. The salient features of the ceramic coating are room-temperature curability, ease of application, minimum weight, durability, erosion resistance, stable optical characteristics, easily repairable, non-contaminating, high purity and high temperature compatibility with silica fabric. The properties of the ceramic coating are weight/area: 0.025–0.030 g/cm2, solar absorptivity the UV–VIS region: 0.12–0.18, IR emittance: >0.86, backwall temperature: <120°C (from kinetic heating simulation test).Keywords
Emissivity, Flexible External Insulation, Protective Ceramic Coating, Reusable Missions.Full Text
References
- Hurwicz, H. and Robert, M., Thermal protection systems – application research of materials properties and structural concepts. Technical Documentary Report No. ML-TDR-64-82, January 1965.
- Emde, W. D., Thermal protection system for the Space Shuttle Orbiter, Technical Report System No. 76–30, Rockwell Space Division, Downey, California.
- Ronald, T. M. F., Materials related to the National Aero-Space Plane, NASP Joint Program Office Aeronautical Systems Centre Air Force Command, Roger D. Launius, Dennis R. Jenkins, Wright-Patterson, AFB, OH, 1994.
- Cleland, J. and Iannetti, F., Thermal protection system of the Space Shuttle, NASA Contractor Report 4227, NASA, USA, June 1989.
- NASA Technical Memorandum, NASA Space Shuttle Technology Conference: Dynamics and Aeroelasticity, Structures and Materials, NASA TM X-2570, San Antonio, Texas, 12–14 April 1972.
- Coleman, W., Dansby, T. and Sheldon, R., NASP technology option six, leading edge cooling. NASP-CR-1082, May 1990.
- Mountvala, A. J., Nakamura, H. H. and Rechter, H. L., Development of lightweight thermal insulation materials for rigid heat shields. Report No. 1, 25 June 1965.
- Mui, D. and Clancy, H. M., Development of a protective ceramic coating for Shuttle Orbiter advanced flexible reusable surface insulation (AFRSI). In Proceedings of the 9th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science, Rockwell International Space Transportation System, Downey, California, 1985, vol. 6 (issue 7/8), pp. 793–805; doi:10.1002/9780470320280,ch31.
- Kourtides, D. et al., Evaluation of thermal control coatings for flexible ceramic thermal protection systems, NASA Technical Memorandum, NASA TM-112199, NASA, USA, July 1997.