New thermal protection system using high-temperature carbon fibre-reinforced plastic sandwich panel

被引:36
作者
Kubota, Yuki [1 ]
Miyamoto, Ousei [2 ]
Aoki, Takuya [1 ]
Ishida, Yuichi [1 ]
Ogasawara, Toshio [3 ]
Umezu, Shinjiro [2 ]
机构
[1] Japan Aerosp Explorat Agcy, 6-13-1 Osawa, Mitakashi, Tokyo 1810015, Japan
[2] Waseda Univ, Grad Sch Mech Engn, Shinjyuku Ku, 3-4-1 Okubo, Tokyo 1698555, Japan
[3] Tokyo Univ Agr & Technol, Dept Mech Engn, 2-24-16 Koganeishi, Nakama, Tokyo 1848588, Japan
关键词
Thermal protection system; Ablator; Weight reduction; Polyimide composite material; Arc-heated plasma wind tunnel test; BACKBONE STRUCTURES; ABLATION; PYROLYSIS; COMPOSITE; MODEL;
D O I
10.1016/j.actaastro.2019.02.004
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Herein, a new lightweight thermal protection system was proposed to reduce the weight of a re-entry capsule. The proposed system employs an ablator as a thermal protection material, and a high-temperature polyimide carbon fibre-reinforced plastic (CFRP) sandwich panel as a structure member. The sandwich panel was designed to exhibit high thermal insulation and good mechanical properties at high temperature, and simultaneously ensure that the ablator has low thickness. Three-point bending was carried out at a high temperature up to 300 degrees C to evaluate shear strength and flexural rigidity of the sandwich panel. Further, the proposed thermal protection system was examined using an arc-heated plasma wind tunnel to evaluate its thermal protection performance and thermal response. The shear strength and the flexural rigidity of this high-temperature structure were 76.8 and 86.9% of that at room temperature, respectively, when evaluated at 300 degrees C. The proposed system achieved more than 40% weight reduction while maintaining high thermal insulation and recession resistance.
引用
收藏
页码:519 / 526
页数:8
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