Mathematics – Logic
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.446t&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Mathematics
Logic
Scientific paper
Due to the foreseen evolution of the satellites market, the increase of Ariane5 performance became a necessity. With a 10t performance, the new A version cryogenic upper stage (ESC-A) is an intermediate step to the development of the B version cryogenic upper stage (ESC-B) forecasted at the end of 2005. To be interesting, the ESC-A stage must be developed in a short time schedule. The reuse of A4 third stage well-known components allows a three years stage development. According to the conclusions of the CNES-ASTRIUM-EADS_LV dynamic working group, the dynamic loads on the payloads and on the launcher must be reduced. After a feasibility study, a non-linear damping device (friction pad system), so called SARO, was designed to fulfil the system and environmental requirements. At cryogenic temperature, this system must allow a static thermal displacement and provide a high damping with small dynamic displacement. The SARO force threshold between linear and non-linear domain was defined as an optimum w.r.t. the payloads dynamic environment. This non-linear device implemented on the launcher is a challenge for the European space industry. From the mechanical point of view, the logic of validation has taken into account this main evolution and therefore it was organised in two steps: Based on two well-controlled tests, the logic wants to avoid the complexity of an upper composite behaviour combined with the flight environment, in a non-linear domain. This paper will present the need identified during the working group and the retained solution. For the validation step, we will focus on the tests. Both tests will be presented. The in-flight efficiency of this device will be estimated by the results of these two tests. The confidence on the in-flight prediction will depend on the correlation between test prediction and test results. Main results will be produced. According to the test/prediction correlation, the methodology applied for the in-flight prediction will be explained.
Breviere F.
Le Gallo V.
Romeuf T.
Toudic S.
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