1. 1 System Definition Review Team III Derek Dalton Megan Darraugh Sara DaVia Beau Glim Seth Hahn Lauren Nordstrom Mark Weaver

2. 2 Design Requirements Alternative fuel: l H 2 Mid-sized –8 passengers Ultra long range business jet –Providing non-stop service between locations such as Los Angeles-Tokyo Range5,700nmi Passengers8 Cruise Speed0.80M

3. 3 Design Mission 0 3 1 4 8 5 6 72 9

4. 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. 5 Concept Generation Concept C Concept I Concept J Concept H

6. 6 Concept Generation ConceptDescription A2 engine, liquid methane, storage in fuselage C3 engine, liquid sodium borohydride, blended wing Dliquid sodium borohydride, std fuselage, t-tail, mid-wing, aft engine F2 engine, hydrogen, std fuselage, under wing tank, Gnuclear power integrated throughout cabin, conventional G550 H2 engine, hydrogen, blended hump, IHydrogen, separate spherical tanks (one in front one in back) JHydrogen, twin boom, side tanks

7. 7 Pugh’s Method Concepts ACDFGH (Datum)IJ Criteria Drag+++-+SS- Manufacturing / Development CostS--+-SS- Operating Cost+SSS+SSS Acquisition CostS-SS-SS- Efficiency (Engine)-SSS+SSS Weight-+SS-SS- Interior DesignS+++-S-+ Safety Perceptions++++-S-+ StabilityS-SS-S-S Positive (+)34333 02 Negative (-)23116 34 Same (S)42550 63

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

9. 9 Hydrogen Benefits: –Low SFC: 0.2 hr -1 Able to complete design mission –Low emissions: H 2 O Disadvantages: –20 % increase in empty weight –14% decrease in L/D –4 X Volume Specific Energy [MJ/kg] Energy Density [10 3 MJ/m 3 ] Approx. SFC [hr -1 ] Hydrogen1208.40.203 Methane50210.48 Bio-diesel43300.6

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

11. 11 Trade Study: GTOW

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

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

14. 14 Selected Concept

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

16. 16 Fuel Storage 11 ft 78 ft 35 ft 8 ft Pax Area 3,4 2 1 Passengers 1 2 4 3 1)D = 8 ft, L = 43 ft, V = 2161 ft^39143 lb LH2 2)D = 3 ft, L = 78 ft, V = 551 ft^32332 lb LH2 3)D = 1.5 ft, L = 78 ft, V = 137.84 ft^3583 lb LH2 4)D = 1.5 ft, L = 78 ft, V = 137.84 ft^3583 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 Fuel Weight = 12273.7 lbs LH 2 Density = 4.23 lbs/ft 3

17. 17 Constraint Diagram Aircraft Constrained by Cruise and Landing Thrust to Weight: 0.26 lb f /lb m Wing Loading: 88 lbs/ft 2 W TO /S(lbs/ft 2 ) T SL /W TO

18. 18 Aircraft Parameters GTOW48,463 lbs S550 ft 2 b70.4 ft W/S88 lbs/ft 2 T/W0.26 S TO 3,700 ft V Cruise 455 kts Acquisition Cost$36.7 Million

19. 19 Comparison Alternate Fuel (Selected Concept) Conventional Fuel (G550) Fuel TypeHydrogenAvGas GTOW48,463 lbs91,000 lbs S550 ft 2 1,137 ft 2 b70.4 ft90.0 ft T/W0.260.338 S TO 3,700 ft5,910 ft V Cruise 455 kts460 kts Acquisition Cost $2005 $36.7 Million $46.0 Million Interior Selected Concept G550 Passengers818 Cabin Length30.5 ft50.08 ft Cabin Height6 ft6.17 ft Cabin Volume per Passenger 150 ft 3 92.7 ft 3

20. 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. 21 Questions ?

22. 22 Additional Information

23. 23 Trade Study Weight Fractions W1/W00.97Taxi/TakeoffHistorical W2/W10.9805Climb Where M is the Cruising Mach assuming initial M = 0.1 W3/W20.85418Cruise where R is range and L/D = 16 W4/W30.99250LandHistorical W5/W40.97TakeoffHistorical W6/W50.9805ClimbHistorical W7/W60.99448Cruise where R is Alt. range and L/D = 16 W8/W70.98739Hold/Loiter where T is 1 hr loiter W9/W80.995LandHistorical W pay = 200*(4 Crew + 8 Pax)

24. 24 Empty Weight & Cost We/Wo = A*W TO a *M Cr b –A = 1.705571, a = -0.0762, & b = 1.1418 [$]Aqcu. = A*W TO a *M Cr b *Range c –A = 577.7389, b = 0.0586, & c = 1.0027

25. 25 Trade Study: Range

26. 26 Cruise Speed at 6000 nmi

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

28. 28 Pugh’s Method Overview 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 Purpose: To generate best aircraft concept using important design criteria which reflect customer needs and engineering requirements

29. 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. 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: –S TO = 1.21*(W/S)/(g*ρ*C Lmax *(T/W)) Landing: –S L = (1.15) 2 *β*(W/S)/(g*ρ*C Lmax *μ) Cruise: –T SL /W TO = (β/α)*[ρ*V 2 *C D0 /(β*(W TO /S)+2/(ρ*V 2 )*1/(π*AR*e)*β*(W TO /S)]

31. 31 Parameter Calculations Wing Area, S [ ft 2 ] –W/S * (W TO ) = 1/S Wingspan, b [ft] –AR = 9 = b 2 / S