A Study on Metallic Thermal Protection System Panel for Reusable Launch Vehicle
- Paper number
IAC-07-C2.4.03
- Author
Mr. Yao Caogen, China Academy of Launch Vehicle Technology, China
- Coauthor
Prof. Lü Hongjun, China Academy of Launch Vehicle Technology, China
- Coauthor
Mr. Jia Zhonghua, China Academy of Launch Vehicle Technology, China
- Coauthor
Mr. Li Haigang, China Academy of Launch Vehicle Technology, China
- Year
2007
- Abstract
A Ni-based superalloy honeycomb thermal protection system (TPS) panel has been fabricated. And a curved Ni-based superalloy honeycomb sandwich has also been fabricated to meet the need of TPS/tank integration for the future reusable launch vehicle (RLV). The preliminary thermal insulation results of a fabricated Ni-based superalloy honeycomb TPS panel (The areal density of this panel is 6.7Kg/m 2, and total height is 32mm) indicate that the maximum temperature of the lower surfaces of the panel is lower 150 degrees centigrade when the temperature of outer surface is held 650 degrees centigrade for 30 minutes. The flatwise tensile strength and compressive properties of a fabricated Ni-based superalloy honeycomb sandwich coupon was studied at room temperature. A multilayered coating has been developed on the surface of the superalloy honeycomb TPS panel for environmental protection and thermal control. The outer layer is ZrO 2+TiO 2 high emittance coating. The in-between layer is aluminium compound oxidation resistant coating. And a diffused layer is formed between the oxidation resistant coating and the base. The oxidation weight-change results show that the weight-change of the Ni-based superalloy honeycomb sandwich with the oxidation resistant coating is extremely small at 1100 degrees centigrade in air for 10h. The emittance layer of the multilayered coating imparts an emittance in excess of 0.85 during exposure at 850 degrees centigrade, which was at least 14% greater than that of the substrate with oxidation resistant alone.
Key words: Metallic thermal protection system, Reusable launch vehicle, Coating, Thermal insulation
- Abstract document
- Manuscript document
IAC-07-C2.4.03.pdf (🔒 authorized access only).
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