Sky By OceanAire

1. Sky By OceanAire PoorviKalaria Roman Maire Andy Grimes Motohide Ho Tara Palmer Greg Freeman Vicki Huff Nick Gurtowski Jack Yang SanjeevRamaiah

2. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

3. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

4. Mission Objectives • Design an aircraft with supersonic capabilities that is able to link major business city pairs. • Compete with other existing aircraft on the market. Aerion Corporation SBJ Dassault Aviation HISAC Team 1 Lockheed Martin QSST Sukhoi S-21

5. System Requirements Review • First and Business class seating • Prime design focuses are cruise Mach number and cruise • efficiency • Will fly only overseas due to FAR36 and to avoid the ill • effects of sonic boom overland • Around 203 units will be sold in order to operate • profitably between 19 city pairs • Still air range is 5450 nmi. • Design cruise altitude is 50,000 ft. • Design maximum cruise Mach number is 1.8 Team 1

6. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

7.  Major Design Requirements • Takeoff field length • Landing field length • Door height above ground • Airframe life • Range • Number of passengers • Cruise Mach number • Cabin volume per passenger • Operating cost • Cruise altitude • Cruise efficiency • Cumulative certification noise • Stall speed • Wing span • NOx emissions Team 1

8. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

9. Aircraft Concept Selection • Pugh’s Method • Evaluation of designs • Process Overview • Choose criteria • Form matrix • Choose datum • Run matrix and evaluate results • Choose new datum • Iterate until “winning concept” is found Team 1

10. Aircraft Concept Selection • Initial Concept Selection • Each group member designed his or her own design • Based on agreed-on categories • Initial Datum • Concorde • Two Iterations Completed • Thirteen concepts evaluated Concept Description Categories • Nose Type • Canards (Yes or No) • Fuselage Design • Wing Type • Engine Placement • Engine Inlet Geometry • Nozzle Geometry • Tail Configuration • Gear Type and Placement • Door Placement Team 1

11. Initial Concept Designs Team 1

12. Initial Concept Designs Team 1

13. Aircraft Arrangement Team 1

14. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

15. Advanced Technologies/Concepts • Components • Engine selection • Inlets • Combustors • Nozzles • Wing tips • Other Technologies • Skin and structural materials • Compression lift Team 1

16. Engine Selection • Supersonic Regime Considerations • Operation power • Limit on pressure ratio • Engine noise • Combustion emissions Team 1

17. Engine Selection • Medium Bypass Turbofans • Variable cycle technology • Superior efficiencies • Higher TSFC • Reduced turbine temperatures Image: "Aircraft Design: A Conceptual Approach" - Daniel Raymer Team 1

18. Combustor Technology • Nox Emissions • Direct functions of Gas temperature • Cannot remain above 3300° F for too long • Unacceptable levels of Nox • Efficient Mixing • Increase full vaporization prior to injection Image: "Engine Design and Challenges for the High Mach Transport" ~ Koff

19. Inlet Design • Ramp Inlet • Variable Inlet Geometry • Mass flow requirements • Shock creation and control Image: "Aircraft Design: A Conceptual Approach" - Daniel Raymer Team 1

20. Inlet Design Analysis • Drag Trends • 2-D Ramp vs. Axisymmetric • Increase in drag Image: "Aircraft Design: A Conceptual Approach" - Daniel Raymer

21. Nozzle Design • Variable Nozzle Geometry • Better match between different operating conditions • Ejector Nozzle • Used with variable geometry Image: "Aircraft Design: A Conceptual Approach" - Daniel Raymer Team 1

22. Wing Tip Inclusion • Advantages • Reduction of the AR during cruise • More stability surfaces • Reflection of the oblique shock (extra compression) • Disadvantages • Extra complexity • Extra weight • May interfere with landing constraints in case of failure Team 1

23. Advanced Concepts: Materials • Factors: • Performance at high temperatures • Skin temperature increases more rapidly at higher speeds • Raymer: 350° average skin temperature at Mach 1.6-1.8 • Affordability • Efficiency • Corrosion • Service Life • Availability Team 1

24. Advanced Concepts: Materials • Aluminum Alloys • Most widely used • Abundant • Moderate cost • Excellent strength-to-weight ratio • High strength: 7075 • Aluminum Lithium Alloy comparable to composites • 250°F maximum operating temperature • Weak in fracture toughness and creep resistance Team 1

25. Advanced Concepts: Materials • Titanium Alloys • High stiffness • Resistant to high temperatures • Corrosion resistant • High strength to weight ratio • Difficult to form • Excessive weight • Expensive (5X aluminum) • Primary use on wing and tail leading edge • Also, engine components and landing gear Team 1

26. Advanced Concepts: Materials • Composites • Weight reduction • Filament-reinforced: high strength to weight ratio and weight savings • Graphite Epoxy (Carbon-fiber composite): high strength-to-weight ratio but very expensive (20X aluminum) • Max temp: 350° Team 1

27. Advanced Concepts: Materials • Composites: • Cannot accept concentrated loads • Strength affected by many factors • Susceptible to damage • Internal damage difficult to find • Difficult to repair • Complex material properties Team 1

28. Advanced Concepts: Materials • Aerion: • Wing: Carbon Epoxy • Leading edge: Coated with metal for erosion resistance • Fuselage: Aluminum & Composites • QSST: • No new “breakthrough” materials • XB-70 • Stainless steel • Sandwiched honeycomb • Titanium Team 1

29. Advanced Concepts: Materials • Next Steps: • 2020: vast advances in composites • Two main focus points: • Weight & temperature • Different materials in different locations • Work with sizing • Determine maximum loads • Look into joints & sealants Team 1

30. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

31. Initial Cabin Layout Team 1

32. Initial Cabin Layout Team 1

33. Initial Cabin Layout Emergency Exit Emergency Exit Emergency Exit Boarding Door Team 1

34. Initial Cabin Layout • First Class Seat Pitch = 46” • Business Class Seat Pitch = 42” • 1 Boarding Door (1R) • 3 Emergency Exits • 2 Lavatories Team 1

35. Initial Fuselage Dimensions • Length = 196’ • Width at Max = 9’ • Width at Tail = 4’ Team 1

36. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

37. Constraint Analysis / Constraint Diagram • Major Performance Constraints: -Cruise • 1g Steady Level Flight, M = 1.8 at h=50,000 ft • Assuming Standard Atmosphere Conditions -Subsonic Maneuver • 2g turn at 250 knots at h = 10,000 ft • Assuming 92% of the take off weight -Takeoff Ground Roll • 6000 ft at h = 0 ft • +15° Hot Day -Landing Ground Roll • 4000 ft at h = 0 ft • +15° Hot Day -Second Segment Climb Gradient • above h = 0 ft • +15° Hot Day Team 1

38. Basic assumptions made for each constraint Team 1

39. Team 1

40. Compression Lift, 3 engines, Non-folding winglets configuration Design: Wing Loading ~ 104 psf Thrust to Weight Ratio ~ 0.515 Team 1

41. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

42. Current Sizing Approach • Writing MATLAB code • Advances the Initial Sizing Spreadsheet • More detailed breakdown of each segment of design mission to get more accurate segment weights, fuel weights • More detailed geometry • Inclusion of Lift, Drag, SFC as functions of geometry, engine specs, altitude, Mach number, etc. Team 1

43. Main Code Inputs TSL/W0, W0/S, W0,guess, SFCSL … etc Determine Other Variables TSL = (TSL/W0)W0 S = W0/(W0/S) We = f(W0, S, TSL, etc) Wfuel = f(W0, S, TSL, etc) W0,guess = W0,new W0,new = Wpay + Wcrew+ We + Wfuel W0,new ≈ W0,guess False True W0 Team 1

44. Example of segment function: Cruise Inputs Vcruise, Rcruise, Wcurrent Wcurrent = W1 i = 1:n Di = f(geometry, Wi, M, h) SFC = f(h,M,D) Li = Wi Calculations Wi+1/Wi = exp[-(Rseg*C)/(V(Li/Di)) Wi+1=Wi*Wi+1/Wi Team 1 Wn+1

45. Component Weight Prediction • Used component weight prediction equations from Raymer 15.3 • Used Concorde as “standard” • Obtained values for variables • Calculated correction factor from Concorde • Published We / Predicted We • Factor = 2.04 • Will be used once more of our variables are found/calculated Team 1

46. Current Values • Based on Initial Sizing Spreadsheet • ARcruise = 1.9 • T/W0 = 0.45 • W0/S = 107 • SFC = 0.78 1/hr • Gross T.O. Weight: 299,100 lbs • Fuel Weight: 169,300 lbs • Total Empty Weight: 118,200 lbs Team 1

47. Next Steps • Include Engine Specs • Find reasonable prediction for wave drag • Employ advanced flight control equations for better prediction of aerodynamic coefficients • Develop Lift, Drag, SFC, etc. functions • Finish Advanced Sizing Code Team 1

48. System Definition Review • Mission Objectives • Design Requirements • Aircraft Concept Selection • Advanced Technologies and Concepts • Initial Cabin Layout • Constraint Analysis and Diagrams • Sizing Studies • Summary of Aircraft Concept Team 1

49. Summary Team 1

50. Summary Requirements Compliance Matrix Table #. Requirements Compliance Matrix to Date Team 1