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) Calculate the distributed load resulting from the 22.05 lb load distributed uniformly across the fuselage frame in inches and calculate the maximum stress in the fuselage frame under the 22.05 lb load in psi.
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:
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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)
-
Calculate the distributed load resulting from the 22.05 lb load distributed uniformly across the fuselage frame in inches and calculate the maximum stress in the fuselage frame under the 22.05 lb load in psi.
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Could you determine the maximum deformation (deflection) of the fuselage frame under the 22.05 lb load in inches and calculate the maximum shear stress in the fuselage frame in psi.?
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