Design and Analysis of a Microsatellite Structure in lowearth Orbit

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.