Jet Aircraft with Manta-ray
Embodiment Semblance
Wide-body Aircraft Next Generation
FINAL PRESENTATION
Tham Jay Shen
Ong Han Yang
Chia Wei Fong
Daniel Hendri
Dikshit Abhijnan
Ong Kai Le
Peranut Foo Yong Li
Introduction
Mission
To significantly reduce carbon emissions of short-to-medium range flights while maintaining cost-effectiveness of airlines
Objective
To design a commercial transport aircraft capable of carrying 156 pax over 6,300 km with 10% carbon-fuel savings per pax
Introduction
1
Market Analysis
Growth in APAC
New Aircraft Demand
Narrow-Body Jet Demand
Fleet Renewal
Flexibility of Low-Capacity Planes
Eco-friendly policies
Jet Fuel Price Volatility
Growing middle-class
Expected annual growth of 5.3%
Flexible fleet size management
Fewer passengers to recoup operational costs
Uncertainty from OPEC actions and economic shocks
Expected higher average fuel prices
Paris Agreement
Cost pressures from environmental policies
Widespread grounding of aircraft
Delayed maintenance impacts airworthiness
Market Analysis
2
Passengers
156
Range
6,300 km
Cruise Speed
830 km/h
Aerodynamics
Dikshit Abhijnan
Propulsion
Stability and Controls
Structural Design
Tham Jay Shen
Daniel Hendri
Systems
Peranut Foo Yong Li
Ong Kai Le
Avionics
Ong Han Yang
3
Aircraft Design
Aerodynamics
Dikshit Abhijnan
VP, Engineering
Aerodynamics Engineer
Airfoil Selection
Eppler 344
Symmetrical NACA 16 Series
Supercritical Airfoils
NACA 64 Series
Main Considerations
Centrebody Airfoil
Outer Wing Airfoil
Trade-off between low drag and greater space
Trade-off between design lift coefficient and shockwave mitigation
NACA 64 Series
Eppler 344
Final Airfoil
Aerodynamics
4
Aerodynamic Design
Sharklet winglet design with angular transition
Tip stall problem in BWB aircraft
Unable to mitigate with twist
Use of vortex generators on tip of the aircraft to delay tip stall
Without twist
With twist
Alternative Stall Prevention Device
Co-flow jet airfoil
Jet of bleed air flowing across airfoil surface of aircraft to re-energize the boundary layer
5
Aerodynamics
Aerodynamic Design
Increasing maximum coefficient of lift
Highly effective Fowler Flaps
Increase coefficient of lift to lower stall speed, improve landing and takeoff performance
Wing Sweep kept between 30-40 degrees
Reduce effective Mach Number
Improve Aerodynamic Efficiency
Pressure Distribution
Front region of the aircraft has low pressure - majority of lift produced
Rear region producing negative lift because of reflex airfoil - acting as a tail
6
Aerodynamics
High Performance Design
Parametric Study for Optimization
Higher Wing Loading - Higher Performance
Higher Aspect Ratio - Higher Performance
Performance Constraint Analysis to ensure adherence with performance goals
Chosen Parameters
43 lbs/ft² and 5.58 chosen as wing loading and aspect ratio to provide optimum performance and meet cabin requirements
Thrust-to-weight ratio of 0.258 needed to meet all performance requirements
7
Aerodynamics
Aerodynamic Performance
Cruise L/D
Maximum L/D
Superior Aerodynamics
Cruise L/D = 20.04
Maximum L/D = 23.10
Complex Drag Calculations
Parasite drag of wing-body and vertical tail combination calculated through OpenVSP
Analytical Drag Calculations
Accounting for Engine Nacelle Drag and Induced Drag
Lower pressure drag due to more streamline airfoil shape of entire aircraft
Lower skin friction drag due to removal of horizontal stabilizer
8
Aerodynamics
Propulsion
Daniel Hendri
Propulsion Engineer
Engine Design and Selection
Modern engines
Propulsion
Two CFM International LEAP-1A engines
One of the best fuel efficiency in class
9
Engine Design and Selection
Under-wing engine placement for quicker and simpler maintenance and replacement
Under-wing mount
Propulsion
10
Sustainability
Future: 100% Sustainable Aviation Fuel
Today: Jet-A1 Fuel
Propulsion
11
Ong Kai Le
Structural Engineer
Structural Design
Cabin Design
Isometric View (Cabin interior)
Overall Dimension and Labels
Structures
12
Furnishing Design
Beacon Clean Lavatory
Interspace Lite
Structures
13
Cargo Design
Height constraint at aft section
Loading Ramp (Maximize utilisation of space)
Side View (Manta - P1)
Side View (Manta - P1)
Structures
14
Stability & Control
Tham Jay Shen
Stability and Controls Engineer
Primary Controls Design
Twin Vertical Tail
Elevators
Ailerons
& Rudders
Primary Controls
15
Stability
CG
NP
Stability
16
Systems
Peranut Foo Yong Li
Systems Engineer
Weather Systems
Systems
17
Environmental Control Systems
Systems
18
Fire Suppression and
Prevention
Systems
19
Avionics
Ong Han Yang
CEO, AirFlyrer
Avionics Engineer
Data Bus Architecture
Combination of ARINC 664 Part 7 and ARINC 825 Architecture
Repetitive Engineering Data
Central Main System
Avionics
20
Integrated Modular Architecture
Integrated Modular Architecture to reduce cost and weight
Integrated Modular Architecture
Avionics
21
Federated Avionics Architecture
Flight Deck
Avionics
22
Aircraft Health Monitoring System
Avionics
23
Aircraft Health Monitoring System
Avionics
24
Business Development
Chia Wei Fong
Chief Financial Officer
Strength
S
High Fuel-savings
-26% (Past-Gen)
-6.7% (Current-Gen)
Easier Cargo Operations
Rampdoor Access for Faster Loading
No Fall Hazard from Cargo Lift Operations
Customer Satisfaction
Safe Environment Features
Protect Personal Space
SWOT Analysis
25
Weakness
W
Lack of Customization
Uncertain Cabin Experience
Virtual vs Physical Windows
Single Change Require Redesign in Multiple Areas
Difficulty Meeting Individual Airline Special Request
SWOT Analysis
26
Opportunities
Threats
O
ESG Funding
15% Annual Growth of ESG Assets
Easier Fund-Raising Exercises
T
Rise in Investor Activism
Management Desperate for Green Solutions
Competition
From More Well-Funded Aircraft Programs
Regulations
Certification Challenges for BWB Design
SWOT Analysis
27
Cost Breakdown
Cost Analysis
Total RDTE Cost:
USD6.7B
28
Target Production Schedule
Cost Analysis
Year | 1 | 2 | 3 | 4 | 5 |
Output (annum) | 80 | 160 | 180 | 190 | 190 |
Output (monthly) | 6.67 | 13.33 | 15 | 15.83 | 15.83 |
5Y-Monthly Output:
13.33
29
“If it can be dreamt, it can be built.”