Design and Analysis of UAV Fuselage

Abstract:

Article Preview

The objective of this paper is to design and analyze a UAV fuselage. The UAV considered in this paper is designed for short-term use and light-weight with mass carrying capacity of 2kg. Firstly, the shape is considered for aerodynamics. Then, the internal system installation, cargo positioning and fuselage structure are designed. Finite element analysis is used for the stress analysis under the landing condition of static model with 3.5g acceleration. The short-term use is specified to be 20 life cycles and the model is verified by the dynamic drop test. The result from finite element analysis shows that the maximum stress is less than the material’s strength with safety factor of 1.1. From the dynamic drop test, the fuselage can safely support the structure under the required life cycles. Therefore, it can be concluded that UAV fuselage can achieve the requirements.

Info:

Periodical:

Main Theme:

Edited by:

R. Varatharajoo, E. J. Abdullah, D. L. Majid, F. I. Romli, A. S. Mohd Rafie and K. A. Ahmad

Pages:

305-309

Citation:

T. Singhanart et al., "Design and Analysis of UAV Fuselage", Applied Mechanics and Materials, Vol. 225, pp. 305-309, 2012

Online since:

November 2012

Export:

Price:

$38.00

[1] D.P. Raymer, Aircraft Design: A Conceptual Approach, fourth ed., AIAA Educational Series, (2006).

[2] T.C. Corke, Design of Aircraft, USA: Pearson Education Inc, (2003).

[3] C.J. Kourloufas, Structural Optimisation of the Fuselage for the ADFA SAE Aero Design UAV, University of New South Wales, (2008).

[4] M.C.Y. Niu, Airframe Structural Design, Conmilit Press Ltd, (1988).

[5] H. Thoeme, M. Irle, M. Sernek, Wood-Based Panels an Introduction for Specialists, Brunel University Press, London, UB8 3PH. England, (2010).

[6] Information on http: /www. carllswoodproducts. com/plywood. html.

[7] F. Hurlimann, R. Kelm, M. Dugas, K. Oltmann, G. Kress, Mass Estimation of Transport Aircraft Wingbox Structures with a CAD/CAE-based Multidisciplinary Process, Aerospace Science and Technology, 15 (2011) 323–333.

DOI: https://doi.org/10.1016/j.ast.2010.08.005

[8] Federal Aviation Administration, Federal Aviation Regulations Part 23 Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Category Airplanes, USA: Federal Aviation Administration, (2004).

DOI: https://doi.org/10.1520/f2505

[9] A.W. Hall, R.H. Sawyer, J.M. Mckay, Study of Ground-reaction Forces Measured during Landing Impacts of a Large Airplane, National Advisory Committee for Aeronautics, Technical Note 4247, Washington, May (1958).