Ace 402 lec 8 max stress
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This document discusses calculating the ultimate bending strength of a fuselage structure. It provides an example problem of determining stresses in the stringers and skin of a fuselage cross-section due to an applied bending moment. The solution involves iteratively calculating the neutral axis position and effective area through trial and error, starting with an initial assumption that all materials are effective in tension. The results of the first trial are then used to refine the model for a second trial. Comparing the results shows an error of 14% in the neutral axis position between the first and second trials.
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The document outlines a 7-day project management training course. Day 1 covers an introduction to project integration management. Later days cover additional topics like scope, schedule, cost, risk management and Scrum. The course aims to help participants understand key project management principles, processes, knowledge areas and the role of the project manager. It emphasizes the importance of integrating all project efforts, balancing scope, time and cost constraints, and addressing stakeholder needs.
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The document outlines the course schedule for a 7-day project management training. Day 2 focuses on project scope management. It defines key scope management terms and processes. The presentation covers planning scope management, collecting requirements, defining the scope statement, creating the work breakdown structure (WBS), and validating scope. Tools for collecting requirements and creating the WBS are also discussed.
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This document discusses shear flow in aircraft structural design. It covers governing equations for shear flow calculations, case studies of shear flow in aircraft fuselages, and methods for calculating moments of inertia and shear flow. The document is a lecture on shear flow given by Dr. Mohamed Elfarran of Cairo University's Aerospace Engineering Department.
Ace 402 lec 12 fueslage shear flow2
The document discusses three cases of aircraft structural loading and the resulting stresses: 1) Pressurization of the fuselage shell, which induces longitudinal and circumferential stresses that depend on the material properties and geometry, 2) Torsional loading of the fuselage shell, which causes shear stresses proportional to the applied torque and cross-sectional properties, and 3) Bending loads on wing spars, which are resisted by shear stresses in the spar webs and normal stresses in the spar caps that depend on the bending moment and section properties.
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This document discusses material properties and bending stresses. It defines key terms like modulus of elasticity, Poisson's ratio, yield stress, and ultimate tensile stress. It explains that plane sections remain plane after bending but rotate, and that the neutral axis experiences no deformation or stress. The location of the neutral axis depends on the material properties and loading conditions. Equations are provided to calculate bending stresses based on the neutral axis location and applied moment. An example problem calculates bending stresses at different points on an airplanes wing. The document also notes that for very high loads above the elastic range, stresses become nonlinear and the neutral axis must be determined through trial and error.
Ace 402 lec 1&2
The document outlines a lecture on fuselage structural design. It discusses iterative methods for calculating effective width and radius of gyration of thin-walled structures. It also covers loads acting on the fuselage, fuselage structure components like stringers and frames, and examples of analyzing stresses in circular fuselage sections. The document concludes by mentioning that stress analysis of wings will be covered next.
Ace 402 lec 5 effective
This document discusses effective sheet width and inter-rivet buckling in aerospace structures. It explains that stringers stiffen wing and fuselage skins, and skins provide stiffness to stringers even when buckling. An effective width calculation accounts for this effect. The document also describes how inter-rivet buckling can occur if rivet spacing is too long, and provides equations to calculate the effective rivet spacing to prevent this issue.
Mpe 209 lec 9 Pressized Vessels
1. The document discusses stresses in thin-walled and thick-walled cylinders. For thin-walled cylinders, the stress is assumed to be uniform throughout the wall. For thick-walled cylinders, the stresses depend on the radius and include circumferential (hoop), radial, and longitudinal stresses.
2. Internally pressurized thick-walled cylinders experience maximum hoop stress and compressive radial stress at the inner surface. The hoop stress decreases and radial stress increases towards zero at the outer surface. Longitudinal stress is uniform across the wall.
3. Externally pressurized thick-walled cylinders experience minimum hoop stress and compressive radial stress at the outer surface
Mpe 209 lec gear Design
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Mpe 209 lec 11 springs
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Ace 402 Airframe Design and Construction lec 12
The document discusses analyzing the stresses and deflections in aerospace shell beam structures like aircraft wings and space habitats. It presents an approach to idealize the cross-section into parts that carry extensional stress from bending and axial loads versus parts that carry shear stress from shear loads and torques. Joint equilibrium equations are developed and the problem is broken into "pure shear" and "pure torsion" cases that are then summed using superposition. Deflections are also analyzed by summing contributions from bending, shearing, and torsion.
Ace 402 Airframe Design and Construction lec 13
The document discusses shear flow analysis of cantilevered wings. It presents equilibrium equations for 1-cell and 2-cell cantilevered wing models. Tables show shear flow analysis results for a 2-cell cantilevered wing with properties such as shear, bending moment, and torque calculated at each cell. Shear correction factors are also discussed.
MEP 209: Design of Machine elements LEC 3
This document outlines material properties testing methods and concepts. It discusses tensile testing to determine material strengths, stress-strain diagrams, elastic modulus, resilience, toughness, statistical variation in properties, effects of temperature and cold working. It also summarizes material classes including metals, plastics, composites and provides examples of common materials like steels, aluminum, titanium, polymers. Key material properties like strengths, moduli and factors affecting properties are defined.
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Ace 402 lec 8 max stress
- 2. Fuselage Structure ➢Given fuselage structure and determine the ultimate bending strength. ➢ Given loads and determine the maximum stresses applied to the fuselage structure. ➢ Given loads and determine the shear flow distribution. ACE - Dr Mohamed Elfarran
- 3. Ultimate bending strength - Example The figure shows a fuselage cross- section. The stringers are arranged symmetrically w.r.t. the fuselage z-axis. The skin and stringer were made from aluminum 2024. The stringer Hight is 1 in. while there area is 0.12 𝑖𝑛2. Calculate the maximum stresses due to a design bending moment 1.6 E6 Ib.in.? Determine the fuselage Margin of safety if the Stringer-skin allowable strength is 32000 psi? ACE - Dr Mohamed Elfarran
- 4. Ultimate bending strength - Example Solution strategy • The given problem is a trail and error problem, because the neutral axis position depends on the applied compressive stresses (unknown), and the applied stresses depends on the fuselage effective area (unknown) which is also depends on the stringer-skin stresses. • Initially, an effective width should be assumed either as a factor of the skin thickness 𝑊𝑒𝑓𝑓 = 30 ∗ 𝑡𝑠𝑘𝑖𝑛 or by assuming linear stress distribution 𝑤𝑒𝑓𝑓 = 1.9𝑡 𝐸 𝜎𝑙𝑖𝑛𝑒𝑎𝑟 • Due to the fuselage symmetry about the z-axis only one-half of the fuselage will be considered in the present analyses. ACE - Dr Mohamed Elfarran
- 5. Ultimate bending strength - Example Solution Procedure – Trial-1 • Calculate total areas of stringer and effective skin. All sheets in tension side are assumed to be effective. 𝐴 = 𝐴𝑠𝑡 + 30 ∗ 𝑡𝑠𝑘𝑖𝑛 ∗ 𝑡𝑠𝑘𝑖𝑛 Area under compression: ACE - Dr Mohamed Elfarran
- 6. Ultimate bending strength - Example Solution Procedure – Trial-1 • Stringer and skin initial position Skin centroid position ACE - Dr Mohamed Elfarran
- 7. Ultimate bending strength - Example Solution Procedure – Trial-1 Buckled skin contribution ACE - Dr Mohamed Elfarran
- 8. Ultimate bending strength - Example Solution Procedure – Trial-1 Buckling stress Buckled skin contribution Z Buckling coefficient r/t 𝐾𝑐 343.75 55.86 19.6 343.75 44.23 16 750 20.27 9 1187.5 12.80 6 1187.5 28.62 12 1187.5 33.35 14 𝒓 = 𝒓𝒔𝒕𝒂𝒕𝒊𝒐𝒏1 + 𝒓𝒔𝒕𝒂𝒕𝒊𝒐𝒏2 2 , 𝒁 = 𝒃2 𝒓 ∗ 𝒕 1 − 𝒗2 , 𝝈𝒄𝒓 = 𝒌𝒄𝝅2 𝑬 ሻ 12(1 − 𝒗2 𝒕 𝒃 2 Z can be obtained from Figure C9.1 This formula can be used for Poisson’s ration 0.3 ACE - Dr Mohamed Elfarran
- 9. ACE - Dr Mohamed Elfarran
- 10. Ultimate bending strength - Example Solution Procedure –Trial-1 Effective area Buckled skin contribution • Calculate the effective factor based on assumed stresses. • Then calculate the effective area for the buckled skin. In our analysis, we will not assume any stresses, instead in the initial trail we will assume all the skins as in tension. ACE - Dr Mohamed Elfarran
- 11. Ultimate bending strength - Example Solution Procedure – Trial-1 All together ACE - Dr Mohamed Elfarran
- 12. Ultimate bending strength - Example Solution Procedure – Trial-1 Skin without buckling Buckled skin ACE - Dr Mohamed Elfarran
- 13. Ultimate bending strength - Example Solution Procedure – Comments • The importance of trial – 1 is to determine the skin in tension and compression which depends on the neutral axis position which also depends on the skin effective width. • In the initial trail we will assume all the stringers and skins are effective. ACE - Dr Mohamed Elfarran
- 14. Ultimate bending strength - Example Solution Procedure – Trial-2 Skin without buckling Buckled skin ACE - Dr Mohamed Elfarran
- 15. Ultimate bending strength - Example Solution Procedure –Trial-2 All together ACE - Dr Mohamed Elfarran
- 16. Ultimate bending strength - Example Solution Procedure –Comments • The results of trail – 1, give the neutral axis position 3.38” below the fuselage center line, and a second moment of area 1470 𝑖𝑛4 . • The results of trail – 2, give the neutral axis position 0.135” above the location from the first trail, and a second moment of area 1489 𝑖𝑛4 . • The error between trail – 1 and trail – 2 can be calculated to be • Error based on the centroid position 𝜖% = 𝑍2 − 𝑍1 𝑍2 𝑥100 = 27.6−24.2 24.2 𝑥100 = 14% ACE - Dr Mohamed Elfarran
- 17. Ultimate bending strength - Example Solution Procedure –Trial-2 All together ACE - Dr Mohamed Elfarran