Computer Science
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.440a&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Scientific paper
The attitude and roll controll system of the new upper stage of ARIANE 5 ESC-A is located in the vicinity of the stage pyro separation system. In order to protect the equipment against high pyrotecnique shock levels, a shock attenuation device has been developed. This shock attenuation device will reduce the shock levels mainly by multiple interfaces and a low suspension frequency to a level compatible with the equipment design. Besides the shock environment, the equipment is exposed to sine and random environments. The transfer function of the equipment suspended on the shock attenuation device has been limited in the resonance amplification to an acceptable Q-factor. Therefore the multiple interfaces are designed with intermediate visco-elasic layers in order to provide additional damping. The visco-elastic material selection is based on stiffness and material loss-factor as well as on its sensitivity with respect to temperature and frequency. Tests with joint elements containing the viscoelastic layers based on rubber and silicon materials have been performed in a frequency range up to 2000 Hz and in a temperature range from -30°C up to 60°C in order to determine the material loss-factor and the shear, the tension/compression as well as the bending stiffness of the joints. Hardmounted sine and random shaker tests are performed to determine the transfer function of the equipped shock attenuation device as well as to qualify it with respect to structural integrity. These tests are performed at different temperatures in a range from -30°C up to +60°C. Finally the Shock attenuation device is implemented in the stage acoustic test and the stage pyro separation test in order to measure the effective resonance amplification under random excitation reflecting the feed back on the primary structure as well as to determine the shock attenuation capability under flight boundary conditions.
Albus Jochen
Schneegass J.
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