Improvement of spacecraft structure Dynamic Characteristics by Using Honeycomb Sandwich panels | ||
| The Egyptian International Journal of Engineering Sciences and Technology | ||
| Article 1, Volume 31, Mechanical Engineering, November 2020, Pages 44-50 PDF (991.59 K) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/eijest.2020.104954 | ||
| Authors | ||
| Dalia N. Ahmed* 1; Alaa A. Abdelrahman2; Mohamed R. Ghazy2; AbouBaker M. El-Hady3 | ||
| 1aeronautics and space sciences department,cairo university, head of mechanical test lab.at Egyptian space aegency | ||
| 2Department of mechanical design and production engineering,Faculty of engineering, Zagazig University, Zagazig 44511, EGYPT | ||
| 3Egyptian Space Agency (EgSA) | ||
| Abstract | ||
| Honeycomb cored structures are considered one of the most efficient composite structures which are commonly used in different industrial applications. These structures are characterized by high strength to weight ratio and good impact resistance thus it is suitable for aerospace structures. Structural properties of honeycomb structure depend on its lower, upper skin sheet thickness, the core material thickness, cell dimension, cell angle and foil thickness. Using of honeycomb structure panels in satellite main structure provide the opportunity to reduce satellite mass in significant manner. This study concerns with the static and dynamic performance of honeycomb sandwich panel structures and its applications in spacecraft construction. This work studies the static and dynamics characteristics of a spacecraft structure including an intermediate plate made of two different materials; the first one with an Aluminum intermediate sandwich plate while the second with honeycomb sandwich plate. The obtained results show that the satellite structure supported with honeycomb intermediate plate produces higher value of the fundamental resonant frequencies compared to the corresponding ones in satellite structure with Aluminum intermediate plate which is better for the launch vehicle requirements. Moreover, the spacecraft structure mass was reduced by around 15%. | ||
| Keywords | ||
| Honeycomb structure; resonant frequency; dynamic performance; spacecraft construction; cell angle; foil thickness | ||
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