Thermal Protection System Materials and Costs for Future Reusable Launch Vehicles

2001 ◽  
Vol 38 (2) ◽  
pp. 294-296 ◽  
Author(s):  
D. J. Rasky ◽  
F. S. Milos ◽  
T. H. Squire
Keyword(s):  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Launch Vehicles ◽  
Reusable Launch Vehicles

CMC thermal protection system for future reusable launch vehicles: Generic shingle technological maturation and tests

2009 ◽  
Vol 65 (1-2) ◽  
pp. 165-176 ◽  
Author(s):  
T. Pichon ◽  
R. Barreteau ◽  
P. Soyris ◽  
A. Foucault ◽  
J.M. Parenteau ◽  
...  
Keyword(s):  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Launch Vehicles ◽  
Reusable Launch Vehicles

scholarly journals Thermomechanical Coupling Analysis and Optimization of Metallic Thermal Protection System

2019 ◽  
Vol 2019 ◽  
pp. 1-14
Author(s):  
Qiuyi Xu ◽  
Shu Li ◽  
Li Wang ◽  
Apeng Dong ◽  
Yang Meng
Keyword(s):  
Mechanical Performance ◽  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Thermomechanical Coupling ◽  
Launch Vehicles ◽  
Optimization Strategy ◽  
Reusable Launch Vehicles ◽  
Design Variables ◽  
The Cost

The metallic thermal protection system (MPTS) is a key technology for reducing the cost of reusable launch vehicles, offering the combination of increased durability and competitive weights when compared with other systems. A two-stage optimization strategy is proposed in this paper to improve thermal and mechanical performance of MTPS while minimizing its weight. Sensitivity analysis is conducted to determine the influence of various design variables, and these variables are classified into two groups according to the results. Three main parameters are optimized in the first-stage optimization, and others are optimized in the second stage. Combining the response surface method with genetic algorithm ensures the computational efficiency of this strategy. Optimum results show that the thermal insulation capability of MTPS is improved by 20% with little mass cost, validating the feasibility of this optimization strategy.

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.

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