Bombardier Challenger 650�CAD Design & Specifications
Presented by Group 3
Structural Design
Fuel Systems
Configuration
Praveen
Discussion
Contents
01
Aircraft Overview
Key features and specifications
02
Structural Design
Load paths and structural elements
03
Configuration Layout
Design considerations and trade-offs
04
Fuel System Design
Tank systems and fuel management
05
Design Specifications
Technical parameters and performance
Ganjare Aavishkar 22AE30010
Aircraft Overview
Bombardier Challenger 650
Ganjare Aavishkar 22AE30010
Ganjare Aavishkar 22AE30010
Front View
Rear View
Top View
Bottom View
Different Views of Aircraft
Aircraft Overview
Challenger 650
Cabin Capacity
10-12
Passengers
Optimized for super-midsize jet.
Prioritizes spacious, luxury cabin.
Balances size and 4,000 NM range.
Abhishek Lakhera (22AE30001)
Structural Design Considerations
Load Path & Structure
Key Concept: Load Path
Direct load transfer from wings to fuselage
Minimize load path length for efficiency
Position heavy components near wing attachment
Primary Structural Components
Forward Bulkhead
Nose structure
Wing Carry through
Wing-to-fuselage
Longerons
I/H-shaped extrusions
Nose Gear
Attachment point
Longerons Design Principles
I- or H-shaped extruded profiles
Run fore and aft, attached to skin
Straight as possible, minimize bends
Place far out to increase bending moment
Design Optimization
Trade studies required
Minimize openings
Concentrate loads
Stringer construction
Meet Meshram (22AE30019)
Jenish Patel (22AE30014)
Fuel System Design
Tank Configuration
Fuel Tank Systems
Multi-tank configuration for optimal weight distribution and range capability
Aux Tank
Center & Saddle
Forward/Rear
Tail Tank
Tail Cone
C.G. Balance
Main Tank
Left & Right
Primary Fuel
Fuel Capacity
Total System Volume
10,000 kg
kg (approx.)
Priyangshu (22AE10048)
Design Specifications
Technical Parameters
Wetted Area Calculations
As t/c = 0.12 (> 0.05) :
Swet = 45.4 x [1.977 + 0.52 x 0.12] = 92.58 m2
True exposed planform = Projected area / cos(dihedral angle)
Wing Geometry
Wing Span
19.6 m
Wing Area
45.4 m²
Aspect Ratio
8.46
Taper Ratio
0.35
Performance Metrics
Max Speed
Mach 0.85
Range
4,000 NM
Service Ceiling
41,000 ft
Takeoff Distance
5,600 ft
Structural Data
Max Takeoff Weight
23,130 kg
Landing Weight
18,800 kg
Max Payload
2,680 kg
Dheeraj (22AE30009)
Future Improvements
Next-Generation Enhancements
Advanced Materials
Composite structure integration
Lightweight alloy applications
Weight reduction optimization
Weight Reduction
10-15%
Aerodynamic Optimization
Winglet enhancements
Fuselage fairing redesign
Boundary layer control
Drag Reduction
5-8%
Fuel Efficiency
Advanced engine upgrades
Optimized flight paths
Energy management systems
Fuel Savings
12-18%
Innovating for the Future: Enhanced Performance, Efficiency, and Sustainability
Apoorva (22AE30004)