Thermal Protection Systems Technology Transfer from Apollo and Space Shuttle to the Orion Program

Manufacturing of Inconel 718 Based Honeycomb Panels for Metallic Thermal Protection Systems

Materials Science Forum ◽

10.4028/www.scientific.net/msf.710.197 ◽

2012 ◽

Vol 710 ◽

pp. 197-202 ◽

Cited By ~ 1

Author(s):

Hanamantray Baluragi ◽

V. Anil Kumar ◽

K. Narasaiah ◽

Shibu Gopinath ◽

P.P. Sinha

Keyword(s):

Thermal Protection ◽

Space Shuttle ◽

Thermal Protection System ◽

Protection System ◽

Front Wall ◽

Honeycomb Core ◽

Thermal Protection Systems ◽

Wide Range ◽

Protection Systems ◽

Three Point Bend Test

Metallic thermal protection system (MTPS) offers significant improvements over the ceramic based TPS for reentry applications. Space shuttle refurbishment time is estimated to be around 17000 man hours between flights. Metallic based TPS can be fabricated easily and provides wide range of design options for TPS. Adaptability and robustness of metallic thermal protection systems offers the potential for reusability. In this work, a unique manufacturing process has been evolved to realize light weight honeycomb panels through corrugation, laser welding and diffusion brazing of faceplates, where in 50 micron thick Inconel718 foil is used for making honeycomb core and 0.2mm thick Inconel718 foil as faceplates. The compression and three point bend test on these panels have shown no debond between faceplates and honeycomb core. 150x150x5mm size honeycomb panels were coated with YSZ and NiCrAlY based Thermal Barrier Coatings (TBC) and high temperature tests have shown thermal resistance of around 570 °C with front wall temperature of 1186 °C and back wall of 533 °C. Also these panels have been characterized for reusability by the testing of same panel at different heat flux levels. Though it is found that honeycomb panel has shown its integrity without debond a certain acceptable level of degradation in coating is observed. Thus Inconel718 based honeycomb panels with TBC coating are proved for use as thermal protection system for reusable launch vehicle systems.

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Ablative Heating Technology in Hypersonic Re-entry Vehicles and Cruise Aircrafts

International Journal of Recent Technology and Engineering - 2 ◽

10.35940/ijrte.c4844.098319 ◽

2019 ◽

Vol 8 (3) ◽

pp. 3007-3014

Keyword(s):

Thermal Protection ◽

Space Shuttle ◽

High Heat ◽

Heat Liberation ◽

Cruise Missile ◽

Thermal Protection Systems ◽

Protection Systems ◽

Heat Loads ◽

Heating Technology ◽

Multiple Strategy

The aim of researches conducted in thermal protection systems in aeronautics and astronautics field of engineering is to generally defend the craft from high heat loads during operation while operating at hypersonic regimes in air and space. The motive of the following composition is to draft a review analysis on ablative heating materials as thermal protective equipment on reusable planetary/atmospheric re-entry vehicles such as a space shuttle, an inter-continental ballistic missile, or a hypersonic cruise missile. The heat liberation can cause much damage to the aircraft/spacecraft whilst operation which is generally beyond repair. It is therefore of utmost importance to research multiple strategy to reduce the effect of shockwaves damage to spacecraft/aircraft materials. We shall initiate the analysis by mentioning some re-usable tile thermal protection system types such as high temperature reusable surface insulation tiles (H.R.S.I), fibrous refectory composite insulation tiles (F.R.C.I), low temperature reusable surface insulation tiles (L.R.S.I) and gradually move on to ablative thermal protection systems with the advent of reinforced carboncarbon’s application in astronautics and aeronautics respectively.

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