著者

福田 泰久 荒谷 貴洋 小柳 潤 山田 和彦

出版者

一般社団法人 日本機械学会

雑誌

年次大会

巻号頁・発行日

vol.2017, 2017

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<p>The reentry capsule is one of the key technologies to support the sample return mission from deep space. The optimization of heat shield design is essential to meet to the weight limit of a reentry capsule, and one of approach to reduce its weight includes an exact predction of the aerodynamic heating environment at the rear heat shield. As an observation of the rear heat shield of "Hayabusa" reentry capsule, overlapped part of single side aluminized polyimide tape remained after the capsule returned to the earth. This fact shows that the actual heat flux during reentry on the rear was much lower than the assumption for heat shield design. In this paper, the heat flux on the rear was identified by the heating tests of the polyimide tape on the ablators using ICP heater. The result indicates that the heat flux on the rear heat shield is less than 20% of the assumption in the design of "Hayabusa" capsule. Furthermore, one dimensional thermal conduction analysis on the similar structure of the rear heat shield was carried out on the basis of its experimental estimation. The results of this analysis show the possibility that the thickness of ablator material for the rear heat shield may be reduced to half at the maximum.</p>