ProblemYou are tasked with analyzing the frame of a bubble fuselage. The frame is 3D printed using PLA material and must be capable of supporting a 22.05 lb load placed within the cabin space, with the direction of the load indicating the direction of deformation. You will need to perform a series of calculations and analyses to ensure that the design meets strength and safety requirements.Data:Frame Dimensions: A blueprint is provided specifying the dimensions and geometry of the bubble fuselage frame. The thickness of the frame its 0.5 inch.Material: The frame will be 3D printed in PLA material. The material properties of PLA are as follows:Young's Modulus (E): 595669.99 Psi.Yield Strength (σy): 9094.01119 Psi.Density (ρ): 10.04515912 lb/in³Load: A 22.05 lb load will be applied within the cabin space, with the load direction indicating the direction of deformationTasks to Perform:( Remmember present the solution process with equations, procedure and results; use Von Mises Method when required)Determine the maximum deformation (deflection) of the fuselage frame under the 22.05 lb load in inches.Calculate the maximum shear stress in the fuselage frame in psi.Determine the maximum principal stress acting on the fuselage frame in psi and its direction.Calculate the equivalent elastic strain and the maximum principal elastic strain in the fuselage frame.Perform a safety factor analysis to determine if the design meets safety requirements. Apply an safety factor of 2.Calculate the distributed load resulting from the 22.05 lb load distributed uniformly across the fuselage frame in inches (The clause has been resolved prior to posting the question, an image is attached.).Calculate the maximum stress in the fuselage frame under the 22.05 lb load in psi (The clause has been resolved prior to posting the question, an image is attached.). 3.97 In1.85 In4.93 In22.05 lb Weight Pushing Down FromInside The Cabin Frame0 In1.05 In5.50 In1.15 In4.20 In3.75 In1.350.15 In1.18 In2 In1.30 In0.30 In0.30 In6.05 InDirection Of The Load22.05 lb Step 1: Give data• Frame Dimensions: A blueprint is provided specifying the dimensionsand geometry of the bubble fuselage frame. The thickness of the frame is0.5 inch.• Material: The frame will be 3D printed in PLA material.Young's Modulus (E): 595,669.99 Psi.Yield Strength (oy): 9,094.01119 Psi.Density (p): 10.04515912 lb/in³.• Load: A 22.05 lb load will be applied within the cabin space, with theload direction indicating the direction of deformation.ObjectiveTo analyze the frame of a bubble fuselage which is 3D printed using PLA ma-terial. The frame should be capable of supporting a 22.05 lb load placed withinthe cabin space. The aim is to ensure that the design meets strength and safetyrequirements by performing a series of calculations and analyses.Step 2: AnalysisThis report presents the analysis of a bubble fuselage frame using Finite ElementAnalysis (FEA). The frame, 3D printed using PLA material, is designed tosupport a load of 22.05 lb. The analysis aims to ensure that the design meetsstrength and safety requirements.Figure 2: Stress distribution in the frame under the applied load.Figure 3: Strain distribution in the frame under the applied load.A: Static StructuralTotal DeformationType: Total DeformationUnit: mTime: 15TMethodologyThe frame was modeled using the provided dimensions. It was then meshedusing tetrahedron elements with an element size of 0.001 mm. The load of 22lb, equivalent to 4.5 N, was applied in the downward direction. The bottomsurface of the frame was treated as fixed. The material properties of PLA, asprovided, were incorporated into the FEA software, ANSYS Structural.0.005421 Mex0.00481870.00421630.0036140.00301170.00240930.0019070.00120470.000602330 Min0.000C075Figure 1: Meshing of the bubble fuselage frame.The finite element analysis (FEA) of the bubble fuselage frame was conductedusing ANSYS software. After subjecting the model to a load of 22.05 lb, thefollowing results were obtained:. Maximum Deformation: 0.0054 m0.100(Figure 4: Deformation of the frame under the applied load.• Maximum Strain: 0.18• Maximum Von Mises Stress: 0.1 MPaIt's essential to ensure that the maximum stress does not exceed the yieldstrength of the PLA material to ensure the structural integrity of the frame.The results indicate that the frame design is within safe limits for the appliedload, ensuring its structural safety and reliability.

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Problem You are tasked with analyzing the frame of a bubble fuselage. The frame is 3D printed using PLA material and must be capable of supporting a 22.05 lb load placed within the cabin space, with the direction of the load indicating the direction of deformation. You will need to perform a series of calculations and analyses to ensure that the design meets strength and safety requirements. Data: Frame Dimensions: A blueprint is provided specifying the dimensions and geometry of the bubble fuselage frame. The thickness of the frame its 0.5 inch. Material: The frame will be 3D printed in PLA material. The material properties of PLA are as follows: Young's Modulus (E): 595669.99 Psi. Yield Strength (σy): 9094.01119 Psi. Density (ρ): 10.04515912 lb/in³ Load: A 22.05 lb load will be applied within the cabin space, with the load direction indicating the direction of deformation Tasks to Perform: ( Remmember present the solution process with equations, procedure and results; use Von Mises Method when required) Determine the maximum deformation (deflection) of the fuselage frame under the 22.05 lb load in inches. Calculate the maximum shear stress in the fuselage frame in psi. Determine the maximum principal stress acting on the fuselage frame in psi and its direction. Calculate the equivalent elastic strain and the maximum principal elastic strain in the fuselage frame. Perform a safety factor analysis to determine if the design meets safety requirements. Apply an safety factor of 2. Calculate the distributed load resulting from the 22.05 lb load distributed uniformly across the fuselage frame in inches (The clause has been resolved prior to posting the question, an image is attached.). Calculate the maximum stress in the fuselage frame under the 22.05 lb load in psi (The clause has been resolved prior to posting the question, an image is attached.).

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Problem

You are tasked with analyzing the frame of a bubble fuselage. The frame is 3D printed using PLA material and must be capable of supporting a 22.05 lb load placed within the cabin space, with the direction of the load indicating the direction of deformation. You will need to perform a series of calculations and analyses to ensure that the design meets strength and safety requirements.

Data:

Frame Dimensions: A blueprint is provided specifying the dimensions and geometry of the bubble fuselage frame. The thickness of the frame its 0.5 inch.
Material: The frame will be 3D printed in PLA material. The material properties of PLA are as follows:
- Young's Modulus (E): 595669.99 Psi.
- Yield Strength (σy): 9094.01119 Psi.
- Density (ρ): 10.04515912 lb/in³
Load: A 22.05 lb load will be applied within the cabin space, with the load direction indicating the direction of deformation

Tasks to Perform:
( Remmember present the solution process with equations, procedure and results; use Von Mises Method when required)

Determine the maximum deformation (deflection) of the fuselage frame under the 22.05 lb load in inches.

Calculate the maximum shear stress in the fuselage frame in psi.

Determine the maximum principal stress acting on the fuselage frame in psi and its direction.

Calculate the equivalent elastic strain and the maximum principal elastic strain in the fuselage frame.

Perform a safety factor analysis to determine if the design meets safety requirements. Apply an safety factor of 2.

Calculate the distributed load resulting from the 22.05 lb load distributed uniformly across the fuselage frame in inches (The clause has been resolved prior to posting the question, an image is attached.).

Calculate the maximum stress in the fuselage frame under the 22.05 lb load in psi (The clause has been resolved prior to posting the question, an image is attached.).

3.97 In
1.85 In
4.93 In
22.05 lb Weight Pushing Down From
Inside The Cabin Frame
0 In
1.05 In
5.50 In
1.15 In
4.20 In
3.75 In
1.35
0.15 In
1.18 In
2 In
1.30 In
0.30 In
0.30 In
6.05 In
Direction Of The Load
22.05 lb

Step 1: Give data
• Frame Dimensions: A blueprint is provided specifying the dimensions
and geometry of the bubble fuselage frame. The thickness of the frame is
0.5 inch.
• Material: The frame will be 3D printed in PLA material.
Young's Modulus (E): 595,669.99 Psi.
Yield Strength (oy): 9,094.01119 Psi.
Density (p): 10.04515912 lb/in³.
• Load: A 22.05 lb load will be applied within the cabin space, with the
load direction indicating the direction of deformation.
Objective
To analyze the frame of a bubble fuselage which is 3D printed using PLA ma-
terial. The frame should be capable of supporting a 22.05 lb load placed within
the cabin space. The aim is to ensure that the design meets strength and safety
requirements by performing a series of calculations and analyses.
Step 2: Analysis
This report presents the analysis of a bubble fuselage frame using Finite Element
Analysis (FEA). The frame, 3D printed using PLA material, is designed to
support a load of 22.05 lb. The analysis aims to ensure that the design meets
strength and safety requirements.
Figure 2: Stress distribution in the frame under the applied load.
Figure 3: Strain distribution in the frame under the applied load.
A: Static Structural
Total Deformation
Type: Total Deformation
Unit: m
Time: 15
T
Methodology
The frame was modeled using the provided dimensions. It was then meshed
using tetrahedron elements with an element size of 0.001 mm. The load of 22
lb, equivalent to 4.5 N, was applied in the downward direction. The bottom
surface of the frame was treated as fixed. The material properties of PLA, as
provided, were incorporated into the FEA software, ANSYS Structural.
0.005421 Mex
0.0048187
0.0042163
0.003614
0.0030117
0.0024093
0.001907
0.0012047
0.00060233
0 Min
0.000
C075
Figure 1: Meshing of the bubble fuselage frame.
The finite element analysis (FEA) of the bubble fuselage frame was conducted
using ANSYS software. After subjecting the model to a load of 22.05 lb, the
following results were obtained:
. Maximum Deformation: 0.0054 m
0.100(
Figure 4: Deformation of the frame under the applied load.
• Maximum Strain: 0.18
• Maximum Von Mises Stress: 0.1 MPa
It's essential to ensure that the maximum stress does not exceed the yield
strength of the PLA material to ensure the structural integrity of the frame.
The results indicate that the frame design is within safe limits for the applied
load, ensuring its structural safety and reliability.

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