Comparative Study of Deployable Satellite Solar Panel Structure between Carbon Fiber Reinforced Polymer and Al-7075 Honeycomb

Abstract

Research Center for Satellite Technology currently develops satellite constellations using deployable solar panels. This satellite will orbit in an equatorial Low Earth Orbit at an altitude of 600 km and inclination of 0°. The objective of this research is to compare the structural performance of Carbon fiber reinforced polymer (CFRP) and Aluminum honeycomb deployable solar panel structures with mass reduction consideration during launch phase. This method starts by determining the requirements from the launcher and then designing the structure base on HDRM location and face material. The design is divided into two types: HDRM on the side and in the center of the panel. Each design employs CFRP and Al-7075 as the face material. Meanwhile, the design uses Al-5056 as the core material. Modal analysis and static analysis are performed to analyze the structural behavior of solar panel structures. The static analysis used in this work is a combination of quasi-static and random load. The obtained result shows the solar panel with CFRP material where HDRM on the side panel provides the best option compared to other designs. The excellent margin of safety (MOS) over the allowable stress on CFRP as face material and Al-5056 as the core material of the solar panel structure can validate the adequacy of this material. The choice of CFRP materials can also reduce the total mass of solar panel structures.