Thermal performance evaluation of REI panel steps and gaps for Space Shuttle thermal protection system

1972 ◽  
Keyword(s):  
Performance Evaluation ◽  
Thermal Performance ◽  
Thermal Protection ◽  
Space Shuttle ◽  
Thermal Protection System ◽  
Protection System

Thermal Performance Evaluation of Cork Phenolic for Nozzle External Thermal Protection System Using 250 kW Plasma Jet Facility

2018 ◽  
Vol 140 (7) ◽  
Author(s):  
L. Aravindakshan Pillai ◽  
N. Sreenivas ◽  
K. Krishnaraj ◽  
Vinay Unnikrishnan ◽  
M. Ajith
Keyword(s):  
Thermal Performance ◽  
Thermal Protection ◽  
Plasma Jet ◽  
Thermal Protection System ◽  
Protection System ◽  
Convective Heating ◽  
Launch Vehicles ◽  
Time Of Application ◽  
The Core ◽  
Long Time

In one of the launch vehicles of ISRO, there are two solid strap-ons attached to the core liquid engine. During the ascent phase, the external nozzle divergent of the strap-ons experiences heating due to radiation from the strap-ons as well as convective heating from the impingement of plumes from the core engine. Hence, the nozzle divergent of the strap-on beyond compliance ring is thermally protected by a coating of PC10 insulation applied over carbon/epoxy structural backup. Though the system worked satisfactorily, application of PC10 had increased the inert weight of each nozzle by 165 kg and took long time for realization. To reduce the inert weight as well as the time of application, precast phenolic based cork sheets (CkP) having lower density than PC10 were selected, as a replacement to PC10. As part of evaluating the thermal performance of the CkP material, specimen level tests with different configurations were carried out in 250 kW plasma jet facility of Vikram Sarabhai Space Centre (VSSC) wherein both the heat flux and the shear stress as expected in flight were simulated simultaneously. At the end of the test program, CkP was found to be superior to PC10 for external thermal protection system (TPS). This paper highlights details of the qualification tests carried out for clearing the cork phenolic system for use in the future launches.

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.

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