1 / 31

System Definition Review Team III

System Definition Review Team III. Derek Dalton Megan Darraugh Sara DaVia Beau Glim Seth Hahn Lauren Nordstrom Mark Weaver. Design Requirements. Alternative fuel: l H 2 Mid-sized 8 passengers Ultra long range business jet

ishana
Download Presentation

System Definition Review Team III

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. System Definition Review Team III Derek Dalton Megan DarraughSara DaViaBeau GlimSeth HahnLauren NordstromMark Weaver

  2. Design Requirements • Alternative fuel: lH2 • Mid-sized • 8 passengers • Ultra long range business jet • Providing non-stop service between locations such as Los Angeles-Tokyo

  3. Design Mission 3 2 7 4 1 8 6 0 5 9

  4. Market Overview • Projected 10-year revenue is $50B for the entire ultra long range market • Acquire 15% market share within 10 years • Approximately 20 aircraft sold annually • $1B in potential annual sales, 2% of total business aviation market • Expect to enter market in 2040 • Assuming $1B in development costs, will break even in 10 years

  5. Concept C Concept H Concept I Concept J Concept Generation

  6. Concept Generation

  7. Pugh’s Method

  8. Trade Study: SFC Range = 6000 nmi Cruise = .80 M Passengers = 8

  9. Hydrogen • Benefits: • Low SFC: 0.2 hr-1 • Able to complete design mission • Low emissions: H2O • Disadvantages: • 20 % increase in empty weight • 14% decrease in L/D • 4 X Volume

  10. Trade Study: Cruise Velocity Range = 5700 nmi L/D = 16 # Pass. = 8

  11. Trade Study: GTOW

  12. Trade Study: Range Range vs. # of Passengers at Design for Varying Mach Range (nmi) L/D = 16 GTOW = 48,463 lbs Cruise at 0.8 M # of Passengers

  13. Trade Study: Cost ($2005) GTOW vs. Range for Varying Mach $60 Mil. $50 Mil. GTOW (1000lbs) $40 Mil. $30 Mil. Cost = $36.7 Million Range (nmi)

  14. Selected Concept

  15. 27’’ 95’’ 48’’ 72’’ 54’’ 67’’ 39’’ 18’’ Cockpit Cabin Length = 35 feet Cabin Width = 7.5 feet = walk in closet = couch = insulation and partition Cabin Height = 6 feet = end table = seat = kitchen area = fold out table = lavatory Fuselage Layout

  16. 2 2 3,4 4 3 11 ft Passengers 8 ft 1 Pax Area 1 35 ft 78 ft Fuel Storage Fuel Weight = 12273.7 lbs LH2 Density = 4.23 lbs/ft3 • D = 8 ft, L = 43 ft, V = 2161 ft^3 9143 lb LH2 • D = 3 ft, L = 78 ft, V = 551 ft^3 2332 lb LH2 • D = 1.5 ft, L = 78 ft, V = 137.84 ft^3 583 lb LH2 • D = 1.5 ft, L = 78 ft, V = 137.84 ft^3 583 lb LH2 • Total: V = 2988.44 ft^3 12641 lb LH2 Nose: 2*8 = 16ft Tail: 3*8 = 24ft Total: 78 + 16 + 24 = 118 ft

  17. Constraint Diagram • Aircraft Constrained by Cruise and Landing • Thrust to Weight: 0.26 lbf/lbm • Wing Loading: 88 lbs/ft2 TSL/WTO WTO/S(lbs/ft2)

  18. Aircraft Parameters

  19. Comparison

  20. Future Consideration • More accurate cost model - especially development costs • Finalize sizing - utilizing FLOPS • Hydrogen Fuel Storage - safety - volume - additional hardware • Avionics Systems Integrations

  21. Questions ?

  22. Additional Information

  23. Trade Study Weight Fractions Wpay = 200*(4 Crew + 8 Pax)

  24. Empty Weight & Cost • We/Wo = A*WTOa*MCrb • A = 1.705571, a = -0.0762, & b = 1.1418 • [$]Aqcu. = A*WTOa*MCrb*Rangec • A = 577.7389, b = 0.0586, & c = 1.0027

  25. Trade Study: Range

  26. Cruise Speed at 6000 nmi

  27. SFC vs. GTOW Non-Cryo GTWO vs. SFC Trade Study Range = 5700 nmi Cruise = 0.8 M # Pass. = 8 L/D = 18.6 GTOW (1000 lbs) SFC (hr-1)

  28. Pugh’s Method Overview Purpose: To generate best aircraft concept using important design criteria which reflect customer needs and engineering requirements • Chose important criteria: 10 - 15 • Cost, drag, weight, interior design, stability, safety perceptions… • Create easy to share matrix of criteria and concepts • Create concepts and share with group • Clarify aspects of proposed design • Chose “datum” • Good concept • Used as source of comparison

  29. Pugh’s Method Overview [cont.] • Compare each concept to datum • Input data to matrix • (+) if concept better than datum, (-) if worse, (s) if same • Evaluate Ratings • Attack negatives and enhance positives • Eliminate negative features, keep positive features • Add hybrid concepts • Select new datum • Re-run matrix • Eliminate inferior concepts • Choose best concept

  30. Constraint Calculations • Thrust to Weight calculated as a function of Wing Loading. • Area above Takeoff and Cruise lines and left of Landing Line gives acceptable Thrust to Weight and Wing Loading. • Minimum thrust to weight and wing loading desired. • Takeoff: • STO = 1.21*(W/S)/(g*ρ*CLmax*(T/W)) • Landing: • SL = (1.15)2*β*(W/S)/(g*ρ*CLmax*μ) • Cruise: • TSL/WTO = (β/α)*[ρ*V2*CD0/(β*(WTO/S)+2/(ρ*V2)*1/(π*AR*e)*β*(WTO/S)]

  31. Parameter Calculations • Wing Area, S [ ft2] • W/S * (WTO) = 1/S • Wingspan, b [ft] • AR = 9 = b2 / S

More Related