@techreport{oai:jaxa.repo.nii.ac.jp:00002322,
 author = {加藤, 純郎 and 菅野, 義就 and 奥山, 圭一 and 上垣, 栄一 and 山田, 哲哉 and 鈴木, 俊之 and Kato, Sumio and Kanno, Yoshitsugu and Okuyama, Keiichi and Uegaki, Eiichi and Yamada, Tetsuya and Suzuki, Toshiyuki},
 month = {Mar},
 note = {The re-entry capsule USERS/REV was successfully recovered in May 2003. REV has a heat shield system to protect inner equipments against the severe heating environment during the re-entry. The heat shield system is mainly made of three kinds of layers, i.e., CFRP ablator, felt type insulation material with thermal anchor and an aluminum shell structure. In the design of the heat shield system, contradictory requirements of heat ejection in orbit and heat protection during the re-entry had to be satisfied. Thermal protection performance of the heat shield system was calculated using an ablation analysis code. Thermal stress analysis of the ablator during the reentry was carried out using a large deformation FEM that considers materials non-linearity. For the development of the heat shield system, various kinds of tests such as the arc-heated tests of the ablator and the strain survey test of the heat shield system were carried out. After the recovery of REV, evaluation of the recovered heat shield system was carried out. The temperature time histories in the ablator obtained during the re-entry and the damage of the heat shield system measured after the recovery were compared with the results of ablation analysis and structural analysis, from which the heating environment during the re-entry and the cause of the damage were estimated. The evaluation of the heat shield system design based on the flight results is also described., 資料番号: AA0048710006, レポート番号: JAXA-RR-04-045},
 title = {REV熱防御系の設計と飛行後解析},
 year = {2005}
}