In this research, the influences of modal properties of a micro cubic satellite on equivalent static loads (due to combination of quasi-static and dynamic loads during launch time) have been studied. The study shows that the magnitude of equivalent static loads can be affected by satellite effective modes and effective mass distribution along natural frequencies. | Nội dung Text Prediction of equivalent static loads act on a micro satellite via modal analysis Engineering Solid Mechanics 3 2015 75-84 Contents lists available at GrowingScience Engineering Solid Mechanics homepage esm Prediction of equivalent static loads act on a micro satellite via modal analysis M. Safarabadia and S. Bazarganb a School of Mechanical Engineering College of Engineering University of Tehran Tehran Iran b Aerospace Engineering Faculty KNT University of Technology Tehran Iran ARTICLE INFO ABSTRACT Article history In this research the influences of modal properties of a micro cubic satellite on equivalent Received October 6 2014 static loads due to combination of quasi-static and dynamic loads during launch time have Accepted 2 February 2015 been studied. The study shows that the magnitude of equivalent static loads can be affected by Available online satellite effective modes and effective mass distribution along natural frequencies. Besides 2 February 2015 when to distinct launchers with different dynamic environments candidate for launch Keywords Quasi-static load analytical results illustrate that sometimes the equivalent static combined load value can be Random vibration higher for the launcher with smaller quasi-static loads. This phenomenon is due to effective Low frequency load modal mass distribution of the satellite. Consequently a higher combined load may be Equivalent static load occurred during launch for smaller quasi-static conditions. Furthermore in separation phase of Shock Phenomenon satellite from the launcher the satellite modal parameters influence the magnitude of applied Modal effective mass shock load in both axial launch and lateral directions importantly. Thus the present study yields reliable input values for separation shock test which considers dynamic properties of the satellite in comparison with some standards and launcher manuals suggest a rough estimation of shock load neglecting the .
