NUMERICAL INVESTIGATION ON THE FUSELAGE AIRFRAME OF LSU 05 NG AIRCRAFT

M Hafid, Abian Nurrohmad, Redha Akbar Ramadhan

Abstract

In this paper, numerical investigation on the fuselage structure of LSU 05 NG was carried out. This fuselage is designed to carry the payload up to 30 kg. Statical numerical analysis using finite element method was done using Simulia Abaqus. The fuselage structure that has been design consists of frame, longeron, and skin that can also be semi-monocoque structure. This airframe use combination of balsa and GFRP type of composite as the material. There are three load case: take-off condition, cruise condition, and landing condition. Tsai-hill failure criteria is used to investigate the strength of the composite structure due to the load that applied. Maximum stress from this calculation is 48 Mpa at the ground condition (take-off and landing) while the cruise stress analysis is 16 Mpa. The maximum tsai-hill criterion is 0,83. With such simulation results it can be said that the fuselage structure is still safe when operated and can also be optimized for several components so that the weight of the aircraft can be reduced.

 

Keywords

finite element method, stress analysis, fuselage, unmanned aircraft

Full Text:

PDF

References

Abdurohman. K, Marta. A, 2016. An Experimental Study of Polyester Composite Tensile Properties Reinforced Undirectional Carbon Fiber Manufactured by Vacuum Infusion for LSU Materials. Jurnal Teknologi Dirgantara Vol. 14 No. 1 Juni 2019 :61-72

Ariyanto. M, Setiawan J. D, Prabowo. T, Haryanto. I, Munadi, 2018. Design of a Low-Cost Fixed Wing UAV. IJCAET & ISAMPE 2017. MATEC Web of Conferences 159, 02045 (2018)

Chen. Y, Lu. X, 2018. Numerical simulation of unmanned aerial vehicle under centrifugal load and optimization of milling ang planning. AIP Conference Proceedings 1967, 040062 (2018)

Chung. P. H, Ma. D. M, Shiau. J. K, 2019. Design, Manufacturing, and Flight Testing of an Experimental Flying Wing UAV. Applied Sciences

Dassault Systemes, 2010. Introduction to Abaqus. Abaqus User Documentations.

Hadjez. F. And Necib. B, 2015. Stress Analysis of an Aircraft Fuselage with and without Portholes using CAD/CAE Process. Journal of Aeronautics & Aerospace Engineering Volume. 4 Issue 1

Hibbeler. R, 2011. Mechanics of Materials. Pearson Prentice Hall.

Isna. L. R, Abdurohman. K, Ula. N. M, Wijaya. Y. G, 2019. Tensile properties E-Glass ±45° Fiber with Matriks Polyesther Composite as Structure of LSU. Iptek Penerbangan dan Antariksa: Progres Litbangyasa Roket, Satelit dan Penerbangan 2018

Raja. D. B. P, et.al, 2018. Stress analysis of Al2014-T6 riveted splice joint fuselage

structure using finite element analysis. IOP Conf. Series: Materials Science and Engineering 455 (2018) 012138

Singhanart. T, Srimontok. C, Pisitpan. N, Chitimaworaphan. S, Mongkhonchaiwiwat. W, 2012. Design and Analysis of UAV Fuselage. Applied Mechanics and Materials ISSN: 1662-7482 Vol. 225, pp 305-309

Velasco. M. F, Stampfli. E, Fardoun. H, Balboa. M. D, 2016. Mechanical Design Project: Conceptual and Preliminary Design of an Unmanned Aerial Vehicle. Universidad Europea de Madrid

DOI: http://dx.doi.org/10.30536/j.jtd.2020.v18.a3327

Refbacks

  • There are currently no refbacks.