@techreport{oai:jaxa.repo.nii.ac.jp:00002716,
 author = {石澤, 淳一郎 and 今川, 吉郎 and 南, 伸太朗 and 馬場, 尚子 and 森, 一之 and Ishizawa, Junichiro and Imagawa, Kichiro and Minami, Shintaro and Baba, Naoko and Mori, Kazuyuki},
 month = {Oct},
 note = {Since spacecraft structures constitute a high proportion of total satellite mass, sandwich panels are commonly used which consist of a honeycomb core and either a CFRP or aluminum skin. Sandwich panels have a high specific rigidity, but are expensive to manufacture. JAXA has developed light weight sandwich panels using integral molding of CFRP-prepreg and light weight plastic foam. This material has good workability, design flexibility and a low cost of manufacture. Research on the material's applicability to space structures is almost completed. In this paper, reported are the results of vibration testing of a 50-kg class satellite assembly using these light weight sandwich panels., 資料番号: AA0048057025, レポート番号: JAXA-RM-04-010},
 title = {軽量構体パネルの研究},
 year = {2004}
}