Project_Phase_4 - 1 Project description The project consists of four phases In each phase you perform a portion of the whole analysis and present

Info iconThis preview shows pages 1–5. Sign up to view the full content.

View Full Document Right Arrow Icon
1. Project description The project consists of four phases. In each phase you perform a portion of the whole analysis and present your results in report. You will be handing in 4 separate reports, one for each phase. 2. The Givens The following design parameters and modeling information are known. Design Parameters for Aircraft Gross Weight of Airplane, W g lb 350000+1000* F g-force (without gust loads) # 2.5 Safety factor # 1.5 Type of Al alloy # Al 2024 Young’s modulus, E ksi 10,600 Yield strength ksi 50 The variable F involved in the calculation of gross weight is the first digit of your UFID. Design Parameters for Wing-box Wing-box Span in 1490+10* L Wing-box root section width, C WBroot in 170 Wing-box root section height in 49 Wing-box root section thickness in 1 Wing-box tip section width, C WBtip in 20 Wing-box tip section height in 10 Wing-box tip section thickness in 0.05 Sweep angle, degrees 30 The variable L involved in the calculation of span is the last digit of your UFID. Design Parameters for Wing (Gust load case) Wing-root chord, C root in 337.25 Wing-tip chord, C tip in 90 Aspect Ratio, A r # 9.3 Wing Gross Area, S sq ft 3129 Wing Sweep angle degrees 30
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Fig.1 The red lines shows the sweep of the wing-box section which you analyze Fig.2 Wing-box 3D model
Background image of page 2
20” Fig.3 Wing-box top view Fig.4 Wing-box root section view 170” 745” (Half span) 170” 49”
Background image of page 3

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Phase 4 Determination of the Crack tip Stress Intensity Factor and Wing-tip Deflection Report: 3 to 4 pages Due: 12/15/2010 Description : Perform a crack tip analysis under the shear stresses and flexural stresses found in the previous phase to find the crack tip stress intensity factor. It is also very important to keep track of the wing-tip deflection. The following steps would be useful to solve this phase of the project: (a) Both flexural stress as well as shear stress has to be taken into account. These values have to be found for the bottom flange. Assume the shear stress value to be the one at the center of the bottom flange for the entire crack. (b) Now stress transformation has to be done to align the stresses along the coordinate system of the crack (see figure 5). This will give the necessary stresses to find the stress intensity factor for different modes. (c) To find the wing-tip deflection consider the equation 2 2 ell d ME I dy  where, is the deflection along the span and y is along the span. M ell is the equation of moment for elliptic lift in terms of y. The moment of inertia in this equation is also a function y as it keeps on changing along the span. Consider the wing to be a cantilever beam to decide the boundary conditions. Here are the items required in this phase of the project: 1. A 1.5 in long through thickness crack has been discovered on the bottom surface of the wing close to the fuselage as shown in the figure below. The crack makes a 45 o angle with the y-axis of the wing (along the span). Determine the stress intensity factor K I for Mode I loading. If the fracture toughness of the alloy used is IC K = 2 4 M P am , would you recommend grounding the airplane?
Background image of page 4
Image of page 5
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 06/06/2011 for the course EAS 4200C taught by Professor Kim during the Fall '09 term at University of Florida.

Page1 / 11

Project_Phase_4 - 1 Project description The project consists of four phases In each phase you perform a portion of the whole analysis and present

This preview shows document pages 1 - 5. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online