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Frontiers of Structural and Civil Engineering

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Front. Struct. Civ. Eng.    2016, Vol. 10 Issue (4) : 394-408    https://doi.org/10.1007/s11709-016-0352-z
RESEARCH ARTICLE
Design concepts of an aircraft wing: composite and morphing airfoil with auxetic structures
P R BUDARAPU1(),Sudhir Sastry Y B3,R NATARAJAN3
1. Department of Aerospace Engineering, Indian Institute of Science, Bangalore 560 012, India
2. Department of Aeronautical Engineering, College of Engineering, Defence University, Ethiopia
3. Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Hyderabad, India
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Abstract

This paper is categorized into two parts. (1) A frame work to design the aircraft wing structure and (2) analysis of a morphing airfoil with auxetic structure. The developed design frame work in the first part is used to arrive at the sizes of the various components of an aircraft wing structure. The strength based design is adopted, where the design loads are extracted from the aerodynamic loads. The aerodynamic loads acting on a wing structure are converted to equivalent distributed loads, which are further converted point loads to arrive at the shear forces, bending and twisting moments along the wing span. Based on the estimated shear forces, bending and twisting moments, the strength based design is employed to estimate the sizes of various sections of a composite wing structure. A three dimensional numerical model of the composite wing structure has been developed and analyzed for the extreme load conditions. Glass fiber reinforced plastic material is used in the numerical analysis. The estimated natural frequencies are observed to be in the acceptable limits. Furthermore, the discussed design principles in the first part are extended to the design of a morphing airfoil with auxetic structure. The advantages of the morphing airfoil with auxetic structure are (i) larger displacement with limited straining of the components and (ii) unique deformation characteristics, which produce a theoretical in-plane Poisson’s ratio of −1. Aluminum Alloy AL6061-T651 is considered in the design of all the structural elements. The compliance characteristics of the airfoil are investigated through a numerical model. The numerical results are observed to be in close agreement with the experimental results in the literature.
Keywords wing design      aerodynamic loads      morphing airfoil      auxetic structures      negative Poisson’s ratio     
Corresponding Author(s): P R BUDARAPU   
Online First Date: 02 November 2016    Issue Date: 29 November 2016
 Cite this article:   
P R BUDARAPU,Sudhir Sastry Y B,R NATARAJAN. Design concepts of an aircraft wing: composite and morphing airfoil with auxetic structures[J]. Front. Struct. Civ. Eng., 2016, 10(4): 394-408.
 URL:  
https://academic.hep.com.cn/fsce/EN/10.1007/s11709-016-0352-z
https://academic.hep.com.cn/fsce/EN/Y2016/V10/I4/394
load case EAS speed (kmph) Mach number load factor
A 651.0 0.518 6.716
C 942.4 0.750 6.716
D 1068.0 0.850 5.034
P 1068.0 0.850 5.340
Tab.1  Typical operating loads experienced by an UAV wing structure
quantity units GFRP
bending strength- Tensile MPa 250
bending strength- Compression MPa 150
shear strength MPa 40
Young’s modulus in the warp direction MPa 20000
Young’s modulus in wept direction MPa 20000
shear modulus MPa 3000
density Kg/m3 1800
Poisson’s ratio none 0.3
Tab.2  Mechanical properties of GFRP considered in the present design Jones [64]; Reddy [63]
Sr. No. detail units value
1 center line chord m 1.2250
2 span m 3.0000
3 area ?m2 2.2695
4 mean aerodynamic chord (MAC) m 0.8532
5 location of LE from nose
(a) center line chord m 2.6850
(b) MAC m 3.0568
6 location of LE and c/4 point above FRL
(a) center line chord m −0.3025
(b) MAC m −0.3025
Tab.3  Typical operating loads experienced by an UAV wing structure
Fig.1  Load distribution at different sections for load case “C” mentioned in Table 1
Fig.2  Distribution of shear force for all the load cases mentioned in Table 1
Fig.3  Conversion of the distributed loads in Fig. 1 into design loads (kg) at various sections for the load case “C” mentioned in Table 1
Fig.4  CP line and Aerodynamic Center line for the load case “C” mentioned in Table 1
Fig.5  Variation of the (a) bending moment and (b) twisting moment with span for all the load cases mentioned in Table 1
Fig.6  Two dimensional layout of the proposed composite wing structure
Sr. No. disttip (mm) front spar (mm) rear spar (mm)
wflange tflange tweb wflange tflange tweb
1 1500 60.0 1.25 3.00 147.0 1.25 2.14
2 1425 60.0 1.25 2.93 141.4 1.25 2.10
3 1275 58.4 1.25 2.77 130.0 1.25 1.97
4 1125 118.9 1.25 2.58 118.9 1.25 1.84
5 975 107.6 1.25 2.37 107.6 1.25 1.70
6 825 96.4 1.25 2.13 96.4 1.25 1.52
7 675 85.2 1.25 1.85 85.2 1.25 1.32
8 525 73.9 1.25 1.53 73.9 1.25 1.10
9 375 62.7 1.25 1.17 62.7 1.25 0.84
10 225 51.4 1.25 0.75 51.4 1.25 0.53
11 75 39.9 1.25 0.29 39.9 1.25 0.21
Tab.4  Spar sizing. Variables wflange and tflange indicate the width and thickness of the flange, respectively. The corresponding variables for the web are denoted by wweb and tweb, respectively
Sr. No. disttip (mm) wskin
b/n spars (mm)		 tskin
(mm)		 wLE
(mm)		 tLE
(mm)		 wTE
(mm)		 tTE
(mm)		 trib
(mm)
1 1500 196.00 1.25 245.00 490.00 4.50 1.25 5.03
2 1425 188.50 1.25 235.63 471.26 4.00 1.25 4.90
3 1275 173.37 1.25 216.72 433.44 3.50 1.25 4.62
4 1125 158.52 1.25 198.15 396.30 3.25 1.25 4.30
5 975 143.53 1.25 179.41 358.82 2.75 1.25 3.93
6 825 128.54 1.25 160.68 321.36 2.25 1.25 3.52
7 675 113.55 1.25 141.94 283.88 1.75 1.25 3.04
8 525 98.56 1.25 123.20 246.40 1.25 1.25 2.50
9 375 83.57 1.25 104.46 208.92 1.25 1.25 1.89
10 225 68.58 1.25 85.73 171.45 1.25 1.25 1.19
11 75 53.17 1.25 66.46 132.93 1.25 1.25 0.44
Tab.5  Sizing of ribs and the skin
Fig.7  Swift gliding at equilibrium. (a) Main forces acting on a swift gliding at a given velocity; (b) turning swift gliding, where L is the lift force, D is the drag force and W is the weight of the swift; (c) skeleton covered with feathers in swept and extended wing of a swift
Fig.8  (a) Non auxetic honey comb structure with positive Poisson’s ratio. (b) Auxetic structure with negative Poisson’s ratio
Fig.9  Auxetic structures considered for the design. Schematics of (a) elliptical and (b) circularcells. Schematic of a unit cell geometry with (c) circular nodes, along with the loads and (d) free body diagram of a ligament in (c)
Fig.10  Finite element models of (a) circular and (b) elliptical, cells. Deformed configuration of the auxetic structure under tensile loads, with (c) elliptical and (d) circular cells
Fig.11  Airfoil with auxetic structure of (b) elliptical cells and (b) circular cells, with chord (C) = 700 mm, A = 110 mm, B = 235 mm and skin thickness T = 1 mm
Fig.12  Finite element model of the airfoil with auxetic structures of (a) elliptical cells and (b) circular cells
Fig.13  (a) Three dimensional solid model and the (b) finite element meshed model of the composite wing structure. Deformed configurations at the (c) First and the (d) second natural frequencies, 43.57 Hz and 71.68 Hz, respectively
Fig.14  Deformed configurations of AAEC at axial loads of 5N and 50N are plotted in figures (a) and (b), respectively, and the corresponding distribution of the von-Mises stresses are plotted in (c) and (d), respectively. The maximum amplitude of the displacement and the stress is mentioned in each picture
Fig.15  Deformed configurations of AACC at axial loads of 5N, 20N, 50N, 100N and 150N are plotted in figures (a)–(e), respectively, and the corresponding distribution of the von-Mises stresses are plotted in (f) and (j), respectively. The maximum amplitude of the displacement and the stress is mentioned in each picture
Fig.16  Comparison of the load-displacement, load-von-Mises stress and von-Mises stress displacement plots of AAEC and AACC
Fig.17  Validation of the load-displacement plots with the experiment Spadoni and Ruzzene [<CitationRef>73</CitationRef>]
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