A copy of this work was available on the public web and has been preserved in the Wayback Machine. The capture dates from 2018; you can also visit the original URL.
The file type is application/pdf
.
FLEXIBLE DYNAMIC MODEL OF ATTITUDE MANEUVERING OF RAZAKSAT® SATELLITE
2015
Jurnal Teknologi
Graphical abstract Abstract In this paper, a dynamic model equation of the RazakSAT ® class satellite three flexible solar panels for three-dimensional dynamic studies is developed based on the coupling deformation field. In the model, each solar panel is flexible and attached to the satellite body via a fixed joint where the assumption of Euler-Bernoulli beam is applied for the solar panels. Lagrange and assumed mode method are used to develop the dynamic model of the RazakSAT ® multi-body
doi:10.11113/jt.v76.5857
fatcat:f6uhtevv3bcrzd63xatfqzz6ka