Abstract:
aerospace is one of the most developed science all over the world and it is
not exclusive to the developed countries. In a country like Sudan with extended
boundaries, huge internal resources never profiteered from this technology. There
are numerous security problems represent some challenges. The main objective of
this study is to design a small microsatellite structure to solve and control those
types of problems.
Microsatellite structure was modelled using SOLIDWORKS then the
structure subjected to static test to obtain the stresses and the deformations the
occurred due the internal components then it followed by dynamic test which
contain modal test in free- free constrain for recognition of natural frequency for
avoiding resonance phenomena and to get the mode shape and fixed-free which
stimulate launching environment. Random vibration was performed using polar
satellite launch vehicle requirements and obtain the stresses and deformations due
the vibration loads. All tests performed using ANSYS program.
Microsatellite mechanical structure was modelled with dimension
250mm*250mm*267mm. analyzed using FEA, on static analysis component
weight regarded as loads in the ground environment, stresses and deformation
obtained with maximum values of 33.153 MPa and 0.388 mm respectively.
Occurred on rack hole for Von Mises stress and on the mid of third tray for
deformation. On dynamic analysis modal test and random vibration were
performed. modal test results are frequencies lay on the range of 112 Hz to 302 Hz
which are acceptable with PSLV launcher. random vibration test was performed to
determine the response of structures. Maximum stress and deformation obtained
was 11.601 MPa and 0.09361 mm respectively.
