Application of the Cost – Risk Network method to the thermal protection system of the Space Shuttle

2006 ◽  
Vol 2 (3-4) ◽  
pp. 231-245 ◽  
Author(s):  
Abigail D. Martin ◽  
Robert J. Abella
Keyword(s):  
Thermal Protection ◽  
Space Shuttle ◽  
Thermal Protection System ◽  
Protection System ◽  
Network Method ◽  
The Cost ◽  
Cost Risk

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

2012 ◽  
Vol 710 ◽  
pp. 197-202 ◽  
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.

Investigation of a washer embedded in an orbiter vehicle tile

1994 ◽  
Vol 52 ◽  
pp. 654-655
Author(s):  
H. S. Kim ◽  
V. J. Cummings
Keyword(s):  
Phase Analysis ◽  
Air Force ◽  
Thermal Protection ◽  
Space Shuttle ◽  
Lower Surface ◽  
Thermal Protection System ◽  
Protection System ◽  
Kennedy Space Center ◽  
Air Force Base ◽  
Kennedy Space

At NASA’s Kennedy Space Center (KSC), an engineering debris team performs a post-landing inspection of the space shuttle orbiter for debris and for anomalies in the thermal protection system. The areas of inspection and debris sampling include the orbiter windows, lower surface orbiter tiles, reinforced carbon-carbon panels of the orbiter wings, and the external tank (ET)/orbiter umbilicals.On October 18, 1989, the space shuttle Atlantis was launched from launch pad 39B at KSC. Atlantis landed on runway 23 at Edwards Air Force Base, California on October 23, 1989. During the post-landing inspection performed October 23-24, 1989, a washer, approximately 1/2 inch in diameter, was found embedded in one of the lower surface tiles forward of the LH2 ET/orbiter umbilical area. The washer was oriented perpendicular to the airflow, and approximately half of the washer protruded into the aerodynamic flow.The washer was submitted to the NASA KSC microchemistry laboratory for examination and elemental and phase analysis.

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