Finite Element Analysis of Wing Design
The present analysis is based upon evaluation and optimization of the structural behavior of wings used in airplanes, as given by advanced material and transport aircraft structure. The main goal is to reduce mass and volume cum the stress and deformation
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Abstract The present analysis is based upon evaluation and optimization of the structural behavior of wings used in airplanes, as given by advanced material and transport aircraft structure. The main goal is to reduce mass and volume cum the stress and deformation in the plane geometry. The main focus of the analysis is on the factor of safety or level of safety, which is optimized to remain constant for both standard and new model. The analysis of the wing is kept organized only as far as structural and stress analysis is concerned. The aerodynamics analysis can be done for this geometry. Keywords Computational fluid dynamics
AMTAS ANSYS Factor of safety
1 Introduction The stiffness/weight is one of the most important factor which describes the reliability and endurance of a wing of an airplane or a drone [1]. Higher stiffness/weight indicates higher reliability and endurance of the wing. Two types of design changes are generally considered to achieve high stiffness/weight ratio: 1. Structural design 2. Aerodynamic design 3. The structural design is mainly based on the change in the geometry of the wing design. The developments have been done in this sector by Vinson in 1986 [2] by using hexagonal cells and honey comb shapes for uniaxial compressive loads. Iyengar and Joshi [3] designed the way for weight optimization by using Nitin Chandola (&) R.S. Rawat Department of Mechanical Engineering, Graphic Era University, Dehradun, India e-mail: [email protected] R.S. Rawat e-mail: [email protected] © Springer Science+Business Media Singapore 2017 R. Singh and S. Choudhury (eds.), Proceeding of International Conference on Intelligent Communication, Control and Devices, Advances in Intelligent Systems and Computing 479, DOI 10.1007/978-981-10-1708-7_57
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Nitin Chandola and R.S. Rawat
Table 1 Parameters of standard design by AMTAS
4.
5. 6. 7.
Bounding box Length X Length Y Length Z Properties
557.97 mm 347.25 mm 28.45 mm
Volume Mass
1.0032 106 mm2 2.7086 kg
reinforced fiber composites. By the introduction of ANSYS, Ubaid [1] found the way of static stress analysis effects the critical zones in a wing of a plane. The introduction of Unmanned Aircraft Vehicle (UAV) researched by Jabur in 2003 [1] was carried out by calculating displacement and stress in ANSYS 5.4. The torsional rigidity also plays a vital role in designing of a wing structure because the decrease in the weight of wing can cause decrease in rigidity [4] The objective of this paper is to curb the problem shown by the advanced material and transport aircraft structure (AMTAS) by only considering structural analysis in static load condition. Parameters of standard design by AMTAS are given by Table 1. The wing model is to be optimized in following categories The basic length of the new wing is taken as standard given by AMTAS The analysis done by using factors during static structural analysis are taken constant for both model The temperature of the wing is considered and not of the environment.
2 Methodology In
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