Robertus Heru Triharjanto, M.Sc, Poki Agung Budiantoro


LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satellite structural model and used by launch authority in its total vehicle modal analysis. The modeling used finite element software, and the simplified honeycomb model is validated using standar plate stiffnes problem. After model validation, the boundary condition as in the LAPAN-A5/ChibaSat deployable system is imposed. The result shows that the stiffness of the deployable solar panel plate has met the launch requirement of PSLV’s auxiliary payload. Therefore, the design mode can be used in the development of LAPAN-A5/ChibaSat.  

Full Text:



Aerospace Specification Metal (ASM) Inc., downloaded Feb. 2017, Alumunium 5052,

Foeckersperger, S., Lattner, K., Kaiser C., Eckert, S., Bärwald, W., Ritzmann, S., Mühlbauer, P., Turk, M., Willemsen, P., 2008, The Modular German Microsatellite TET-1 for Technology On-Orbit Versification, Proc. IAA Symposium on Small Satellite Systems and Services, Rhodes, Greece

Halle, W., Hetscher, M., Terzibaschian, T., 2015, The DLR-Satellite BIROS for Fire-Detection and Technological Experiments, 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany

Huzain, F.M., Triharjanto, R.H., 2013, Pengukuran Karakteristik Dinamika Struktur Satelit LAPAN-ORARI/A2, Jurnal Teknologi Dirgantara, Vol.11 No. 2

Kuwahara, T., Sakamoto, Y., Yoshida, K., Takahashi, Y., Fukuhara, T., Kurihara, J., 2011, Mission and System of the Earth Observation Microsatellite Rising-2, 8th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany

Onta, S., Dag, S., Gokler, M.I., 2007, Structural Finite Element Analysis of Stiffened and Honeycomb Panels of the RASAT Satellite, Proc. 3rd International Conference on Recent Advances in Space Technologies

Paik, J.K., Thayamballi, A.K., Kim, G.S., 1999, The Strength Characteristics of Aluminium Honeycomb Sandwich Panels. Thin-Walled Structure, 35:205-231.

Plascore, downloaded Feb. 2017, PAMG-XR1 5052 Aluminum Honeycomb,

SSTL, downloaded Jan. 2016, Solar Panel and Sollar Panel Aseembly,

Triharjanto, R.H., 2006, Desain Dan Pengujian Struktur Satelit Mikro LAPAN-TUBSAT, Jurnal Teknologi Dirgantara, Vol. 4 No. 2

Triharjanto, R.H., Budiantoro, P.A., Yanto, D., Sri Sumantyo, J.T., 2018, The Design Progress of LAPAN-Chiba University SAR Micro-Satellite, submitted for 3rd IEEE ICARES, Bali, Indonesia


  • There are currently no refbacks.