@inproceedings{oai:jaxa.repo.nii.ac.jp:00038631,
 author = {寺島, 啓太 and 紙田, 徹 and Horie, Youichi and Kobayashi, Masakazu and Onikura, Hiroki and Terashima, Keita and Kamita, Toru and Horie, Youichi and Kobayashi, Masakazu and Onikura, Hiroki},
 month = {Sep},
 note = {15th European Space Mechanisms & Tribology Symposium - ESMATS 2013（September 25-27, 2013.), Noordwijk, The Netherlands., This paper presents the design, analysis and test results of the low-shock payload separation mechanism for the H-IIA launch vehicle. The mechanism is based on a simple and reliable four-bar linkage, which makes the release speed of the marman clamp band tension lower than the current system.The adequacy of the principle for low-shock mechanism was evaluated by some simulations and results of fundamental tests. Then, we established the reliabilitydesign model of this mechanism, and the adequacy of this model was evaluated by elemental tests. Finally, we conducted the system separation tests usingthe payload adapter to which the mechanism was assembled, to confirm that the actual separation shock level satisfied our target., 資料番号: AC1400052000},
 publisher = {European Space Agency(ESA)},
 title = {DEVELOPMENT STATUS OF LOW-SHOCK PAYLOAD SEPARATION MECHANISM FOR H-IIA LAUNCH VEHICLE},
 year = {2013}
}