Resumo

VAN DER WESTHUIZEN, K.; BASSON, A.H.  e  SCHUSTER, H.R.. SUNSAT baseplate design, finite element analysis and manufacturing. R&D j. (Matieland, Online) [online]. 1995, vol.11, pp.51-60. ISSN 2309-8988.

The design, finite element analysis, and testing, of the aluminium baseplate and payload adapter assembly of Sun-sat are described. The primary design requirements for the baseplate are that the cantilevered modes' lowest natural frequency for the complete satellite, mounted rigidly on the payload adapter assembly, must exceed 70 Hz, and that 10 g accelerations must be sustained. A finite element model of the payload adapter, baseplate, and lowest tray, with the remainder of the satellite represented by a concentrated mass, was used to optimize the rib configuration in the baseplate. In a subsequent finite element analysis of the complete satellite structure, the first two lateral bending modes were found to be 70.0 and 70.5 Hz. Modal survey tests gave corresponding measured frequencies of 65 and 68 Hz. Mathematical model correlation and the results obtained thereby are described. Strength design requirements, analysis and testing procedures for design verification are outlined.

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