Aac Interiors Design
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AAC INTERIORS DESIGN
WORK FLOW PROCESS at AAC FLOOR SCHEMATIC
ELEVATIONS
SHELL MODELS FOR PRELIMINARY STRESS ANALYSIS
ASSEMBLY
COMPONENT INSTALLATION
INSTALLATION
2
1. FLOOR SCHEMATIC: •
Final approved drawing after the mutual agreement between the AAC Interiors Design team and the end Customer.
•
It is Plan view of the entire aircraft showing the monuments locations in different zones.
3
2. ELEVATION DRAWINGS: •
These are drawings of each zone having plan view of the zone and different sectional views showing the overall dimensions and locations of the monuments.
•
It also gives the information of the materials and vendors for the component manufacturing.
•
Created by the Interior Design team at AAC.
•
It is elaborated drawing of floor schematic created currently in AutoCAD.
4
3. SHELL MODELS FOR STRESS ANALYSIS: •
Shell is the basic structure which carries loads.
•
It is assembly of panels which are honey combed structured. The material could be aluminium or Nomex.
•
Create 3D model of the monuments in Solid works. It is treated as a single inseparable assembly.
•
Do the Stress analysis for the shell models.
SIDELEDGE
BULKHEAD
5
VANITY
CABINET
6
ASSEMBLY OF ALL THE SHELL MODELS
7
ACTUAL FABRICATED SHELL ASSEMBLIES AT AAC
Example Shell Structure: Toilet Shroud
Example Shell Structure: Cabinet
8
4. Assembly creation: •
It is assembly of the shell, doors (wherever applicable), access panels (wherever applicable) & the necessary hardware, hinges & latches.
•
The drawing is the output which is required for the manufacturing and fabrication. Door hinges
Door lid Support
Door Latches
9
5. COMPONENT INSTALLATION: •
It is installation of the components to the assembly model.
•
Components could be oxygen module, Snake/flex lights, reading lights, wash lights.
•
The output is the drawing which gives the detailed instruction of each component installation. Oxygen Module Overhead-Cabinet Assy.
Circuit-Breaker Panel Lights
Reading Lights
Snake Lights
Air-Gaspers
10
5. INSTALLATION: •
It is installation of the total assembly with its components installed into the aircraft structure.
•
This requires standard parts like tie-rods, fittings, insert-screw & floor attachments. STRINGERS
FRAMES
BULIKHEAD
FLOOR OVERHEAD-CABINET SOLIDWORKS 3D-MODEL OF OVERHEAD CABINET INSTL PRODUCT
11
Inserts with screw attachment to bulkhead
Tie-Rod
12
Provision for lower attachment
13
SIDE LEDGE OTTOMAN
ASSEMBLY
14
FINITE ELEMENT MODEL OF SIDE LEDGE SCOPE Finite Element Modeling and Analysis of Side ledge
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stresses, displacements and Reaction Forces
15
FINITE ELEMENT MODEL OF OTTOMAN SCOPE Finite Element Modeling and Analysis of Ottoman
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stresses, displacements and Reaction Forces
16
FINITE ELEMENT MODEL OF OTTOMAN AND SIDE LEDGE ASSEMBLY SCOPE Finite Element Modeling and Analysis of Side ledge and Ottoman Assembly
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stresses, displacements and Reaction Forces
17
FINITE ELEMENT MODEL OF CABINET ASSEMBLY SCOPE Finite Element Modeling of Cabinet Assembly
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Finite Element Model with loads and boundary conditions
18
FINITE ELEMENT MODEL OF GALLEY SCOPE Finite Element Modeling of Galley
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Finite Element Model with loads and boundary conditions
19
FINITE ELEMENT MODEL OF BULK HEAD SCOPE Finite Element Modeling and analysis of Bulk head
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Displacement and Stress
20
DISPLACEMENT CONTOUR OF BULK HEAD SCOPE Finite Element Analysis to find bending stress due to internal loading at critical panel
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stress contour of the component
21
HAND CALCULATIONS –PIN SCOPE Check for PIN
INPUTS Check Pin The pin is heat treated to Ftu = 160 ksi and has the diameter of 0.312in. The longest moment arm of the two pins is used for analysis.Figure – Bolt Bending Single shear allowable = 7,290 lbs t1 = 0.08 in t2 = 0.48 in g = = 0.20 in b = = 0.36 in Moment = 92,565 psi
• Geometric details of the pin and panels • Loading instruction
OUTPUTS • Moment and Margin of Safety
M.S. (bolt bending) = = +0.29
22
HAND CALCULATIONS –FITTING ATTACHMENT SCOPE Check for Fitting Attachment
INPUTS • Geometric details of Fitting Attachment • Loading instruction
OUTPUTS • Shear load and Margin of Safety Pin shear allowable = 2005 lbs Pin tensile allowable = 1940 lbs Collar tensile allowable = 1400 lbs Shear load = 503.4 lbs M.S.(pin shear load) = = +1.99 23
WORK FLOW PROCESS at AAC FLOOR SCHEMATIC
ELEVATIONS
SHELL MODELS FOR PRELIMINARY STRESS ANALYSIS
ASSEMBLY
COMPONENT INSTALLATION
INSTALLATION
2
1. FLOOR SCHEMATIC: •
Final approved drawing after the mutual agreement between the AAC Interiors Design team and the end Customer.
•
It is Plan view of the entire aircraft showing the monuments locations in different zones.
3
2. ELEVATION DRAWINGS: •
These are drawings of each zone having plan view of the zone and different sectional views showing the overall dimensions and locations of the monuments.
•
It also gives the information of the materials and vendors for the component manufacturing.
•
Created by the Interior Design team at AAC.
•
It is elaborated drawing of floor schematic created currently in AutoCAD.
4
3. SHELL MODELS FOR STRESS ANALYSIS: •
Shell is the basic structure which carries loads.
•
It is assembly of panels which are honey combed structured. The material could be aluminium or Nomex.
•
Create 3D model of the monuments in Solid works. It is treated as a single inseparable assembly.
•
Do the Stress analysis for the shell models.
SIDELEDGE
BULKHEAD
5
VANITY
CABINET
6
ASSEMBLY OF ALL THE SHELL MODELS
7
ACTUAL FABRICATED SHELL ASSEMBLIES AT AAC
Example Shell Structure: Toilet Shroud
Example Shell Structure: Cabinet
8
4. Assembly creation: •
It is assembly of the shell, doors (wherever applicable), access panels (wherever applicable) & the necessary hardware, hinges & latches.
•
The drawing is the output which is required for the manufacturing and fabrication. Door hinges
Door lid Support
Door Latches
9
5. COMPONENT INSTALLATION: •
It is installation of the components to the assembly model.
•
Components could be oxygen module, Snake/flex lights, reading lights, wash lights.
•
The output is the drawing which gives the detailed instruction of each component installation. Oxygen Module Overhead-Cabinet Assy.
Circuit-Breaker Panel Lights
Reading Lights
Snake Lights
Air-Gaspers
10
5. INSTALLATION: •
It is installation of the total assembly with its components installed into the aircraft structure.
•
This requires standard parts like tie-rods, fittings, insert-screw & floor attachments. STRINGERS
FRAMES
BULIKHEAD
FLOOR OVERHEAD-CABINET SOLIDWORKS 3D-MODEL OF OVERHEAD CABINET INSTL PRODUCT
11
Inserts with screw attachment to bulkhead
Tie-Rod
12
Provision for lower attachment
13
SIDE LEDGE OTTOMAN
ASSEMBLY
14
FINITE ELEMENT MODEL OF SIDE LEDGE SCOPE Finite Element Modeling and Analysis of Side ledge
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stresses, displacements and Reaction Forces
15
FINITE ELEMENT MODEL OF OTTOMAN SCOPE Finite Element Modeling and Analysis of Ottoman
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stresses, displacements and Reaction Forces
16
FINITE ELEMENT MODEL OF OTTOMAN AND SIDE LEDGE ASSEMBLY SCOPE Finite Element Modeling and Analysis of Side ledge and Ottoman Assembly
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stresses, displacements and Reaction Forces
17
FINITE ELEMENT MODEL OF CABINET ASSEMBLY SCOPE Finite Element Modeling of Cabinet Assembly
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Finite Element Model with loads and boundary conditions
18
FINITE ELEMENT MODEL OF GALLEY SCOPE Finite Element Modeling of Galley
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Finite Element Model with loads and boundary conditions
19
FINITE ELEMENT MODEL OF BULK HEAD SCOPE Finite Element Modeling and analysis of Bulk head
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Displacement and Stress
20
DISPLACEMENT CONTOUR OF BULK HEAD SCOPE Finite Element Analysis to find bending stress due to internal loading at critical panel
INPUTS • 3D Solid Models • Loads, Boundary conditions and Stress work instruction
OUTPUTS • Stress contour of the component
21
HAND CALCULATIONS –PIN SCOPE Check for PIN
INPUTS Check Pin The pin is heat treated to Ftu = 160 ksi and has the diameter of 0.312in. The longest moment arm of the two pins is used for analysis.Figure – Bolt Bending Single shear allowable = 7,290 lbs t1 = 0.08 in t2 = 0.48 in g = = 0.20 in b = = 0.36 in Moment = 92,565 psi
• Geometric details of the pin and panels • Loading instruction
OUTPUTS • Moment and Margin of Safety
M.S. (bolt bending) = = +0.29
22
HAND CALCULATIONS –FITTING ATTACHMENT SCOPE Check for Fitting Attachment
INPUTS • Geometric details of Fitting Attachment • Loading instruction
OUTPUTS • Shear load and Margin of Safety Pin shear allowable = 2005 lbs Pin tensile allowable = 1940 lbs Collar tensile allowable = 1400 lbs Shear load = 503.4 lbs M.S.(pin shear load) = = +1.99 23
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