SCHOOL OF AERONAUTICS AND ASTRONAUTICS Optoprime Conceptual Designs

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Optoprime Conceptual Designs, LLC. “OP-5 -9 -08” Team 2 AJ Berger Colby Darlage Joshua Dias Ahmad Kamaruddin Pete Krupski Josh Mason Camrand Tucker 1 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Co. DR Outline • • • • Major Design Requirements Market Analysis Design Mission Materials and Structures Propulsion Sizing Layout Aerodynamics Reliability Weights and Balances Dynamics and Control Cost Future Considerations 2 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Major Design Requirements Josh Mason 3 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Mission Statement To satisfy our customers through the design of an advanced mid-range aircraft capable of relieving congestion at major hubs throughout the world. The aircraft will: • Operate from lesser-equipped airports throughout the world. • Maintain a high cruise speed while limiting negative impact on the environment. • Satisfy customer needs without sacrificing safety. • This “OP-5 -9 -08” will revolutionize the future market with its high reliability, exceptional comfort, and high profitability – three difficult aspects to master 4 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Walk-Around Chart Trailing Edges • Direct Side Force Capability Aft-Mounted Engines • Rotor Path behind PAX compartment • Fuselage Noise Reduction Flight Deck • No Onboard Operator • Passenger Observation Deck Joined Wing • Drag Reduction • Structural Weight Savings COMPANY CONFIDENTIAL Composite Structure • Weight savings • Corrosion Resistance • Increased Fuel Capacity • Increased Window Size Accessibility • Easy Jetway Access • Capability for Large Cargo Door • No Special Ground Crew Equipment Required 5

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Major Design Requirements Design Criteria Compliance Matrix • • • Short Runway Energy Efficiency PAX Climate/Comfort Range Gate Time Easy Maintenance Low Noise Limited Terminal Service Obstacle Clearance Crew Cost Requirement Target Threshold Current 67442. 4 75376. 8 70900 100 90 100 Balanced Field Length (ft) < 2500 < 3000 2500 Range (NM) >2500 >2000 SFC (lb/lb*hr) < 0. 6 < 0. 7 0. 2 Thrust Available (lbf) 40000 25000 26000 110 106 3 4 3 TOGW (lb) Number of PAX Low Noise (d. B) Crew Members (# of People) COMPANY CONFIDENTIAL 6

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Market Analysis & Design Missions Josh Mason 7 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Market Review Asia-Pacific Potential • 2058 Market • Asia, Australia, Africa • Customer Needs – – Short Runways Cost Effective Low Environmental Impact No Specialized Ground Handling Equipment (BCMO 2007) Africa Potential (AGMF 2007) Airbus 2006 Global Market Forecast: “It is possible that the next ‘India’ will come from this region (Africa). ” 8 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Use Case Scenario 1 • Hong Kong to Madras, India (2000 nm) – ESTO from Hong Kong (3, 000 ft, upwind section of runway) – Extended Range Cruise – ESL at Madras (6, 000 ft runway) Hong Kong Madras COMPANY CONFIDENTIAL ADS-B Continuous Descent Approach & Full Stop Landing Takeoff & Climb Cruise Climb 9

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Use Case Scenario 2 • Sydney (8, 000 ft) to Perth (11, 200 ft) (1769 NM) – refueling/reload • Perth to Coober Pedy (4, 685 ft) (900 NM) – without refueling • Coober Pedy to Sydney(893 NM) Cruise Climb Coober Pedy Perth COMPANY CONFIDENTIAL Descent Sydney Reconfigure to Cargo, Reload with Refuel Descent Climb Reload without Refuel Descent to Full Stop 10

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Use Case Scenario 3 => Design Mission • • • Gary (3000 ft) to Boulder (4100 ft) (793 NM) Rerouted to Durango (9200 ft) (218 NM) Rerouted back to Boulder (Lands and refuels) Gary Boulder Durango Full Stop Landing Climb Descent Loiter Cruise Climb COMPANY CONFIDENTIAL Cruise Climb 11

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Materials, Structural Analysis & Propulsion Colby Darlage 12 COMPANY CONFIDENTIAL

Material Selection SCHOOL OF AERONAUTICS AND ASTRONAUTICS • Ribs : Carbon Fiber Reinforced Plastic (CFRP) • if 38% structural weight made from composites • 40% reduction in empty weight • 39% reduction in wing area • 33% fuel saving • Stringers : Carbon Fiber Reinforced Plastic (CFRP) • Wing Spars : Carbon Fiber Reinforced Plastic (CFRP) • Wing/Fuselage Skins : Central Reinforced Aluminum (Centr. AL) • Wing-weight reduction 20% more than (CFRP) • Simple Repairs • Landing Gear : Titanium Alloy Ti-10 V-2 Fe-3 Al • Higher corrosion resistance and component reliability than steel 13 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Structural Layout • load path - wing box carry through • longerons - 2 below cabin flow - 2 above head height - bonded to composite skin 14 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Preliminary Propulsion Design • Power Plant – 13, 000 lbf per engine • Unducted Fan • Wave rotor combustion • Dual Rotor – – – – 35% TSFC Reduction 15% TSFC Reduction BPR = 35 OPR = 30 TSFC = 0. 2 Weight = 2100 lb each www. flug-revue. rotor. com • Fuel – Synthesized Fuel • • • Fischer-Tropsch-type Green Freedom™ Synthesized from atmospheric CO 2 and H 2 O from nuclear power plant cooling towers Eliminates environmental issues Carbon Neutral Electrical system supplemented by solar power AIAA-2002 -3916 -938 15 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Environmental Impact • Engine noise level reduction expected over the next 50 years • Under current US noise level restrictions • Fischer-Tropsch-type process eliminates traditional kerosene fuels synthesized fuel (addresses oil shortage) • Green Freedom™ Synthesized from atmospheric CO 2 and H 2 O from nuclear power plant cooling towers Eliminates environmental issues Carbon Neutral 16 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Sizing and Reliability Joshua Dias 17 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Sizing Assumptions • FLOPS – Weight Estimates – Mission Profile Analysis – Assumptions: • • • Start with “Average Aircraft” 100 Pax Mcruise = 0. 78 AR = 6 (initial) T/W = 0. 3 (initial) W/S = 100 psf 18 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Weight Breakdown FLOP S Raym e r Roska m Technolo gy Factor Correcte d Weight Fuselage 5847 8628 3400 0. 75 4900 Forward Wing 5200 4800 3200 0. 75 3600 Aft Wing 1063 1500 900 0. 95 1100 Vertical Tail 1500 700 300 0. 7 700 Engine / Nacelle 4862 5500 2600 1 4200 Fuel System (Including Plumbing) 1500 800 3600 0. 85 1700 Landing Gear 2300 500 2200 0. 95 1600 Component Luggage 4000 APU 150 Battery 1500 Furnishings, Seats, Other Misc. 1000 19 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Reliability • High composite usage – Easy to diagnose & repair – Resists corrosion • New Automated Flight Control System www. ventureaviation. ca – Eliminates human error – Has the redundancy of Human-in-the-Loop www. af. mil 20 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Layout and Aerodynamics AJ Berger 21 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Overall Dimensions 81’ 33’ 125’ 22 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Internal Layout • • • 20 Passengers Per Section 30 in Aisle 5 ft from floor to overhead bin Large Overhead Bins 7 ft 9 in from floor to Ceiling 23 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Airport Servicing Map Gate-check Luggage No Pedestrian Zone ay w t Je Fwd Luggage GPU Aft Luggage (if available) Pushback Taxi Lav Service H 2 O PAX Service Fuel • • COMPANY CONFIDENTIAL Easy access for service vehicles 5 Emergency Exits, 2 over the wing 24

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Airfoil • • NASA SC(2)-0612 L = 75000 lbs – Requires a Cl of 0. 55 • • Cruise Cl = 0. 55 Clα=0. 5 = 0. 55 25 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS CL vs. Alpha • Clean Clmax = 2. 2 • Clean CLmax= 1. 7 • Triple Slotted Flaps 1. 9 c’/c • Slats 0. 4 c’/c • Full Flaps/Slats CLmax = 4. 9 26 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS High Lift Devices • Triple Slotted Fowler Flaps – 1. 9(c’/c)=2. 47, c’/c = 1. 3 – Delta_CLmax= 1. 56 • Slats –. 4(c’/c) =. 44 c’/c = 1. 1 – Delta_CLmax=. 396 *http: //www. desktopaero. com *www. answers. com/tpoic/sla ts. htm • Total CLmax= 4. 74 – With Technology Factor, 30% – CLmax= 1. 7 + 1. 95 = 3. 65 * 1. 3 27 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Drag Polar • Clean Configuration Polar – CD_o = 0. 0421 • • Wetted area Fuse = 3482. 1 sqft Wetted area Nose = 300 sqft Wetted area Wing = 2471 sqft Wetted area Engine = 1428 sqft – CD_i = 0. 0150 – CDw = 0. 0028 • L/D cruise = 17 28 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Performance • • • V-n diagram Best range = 2200 Nm Best endurance = 4 hrs Max speed = 815 ft/s Stall speed = 123 ft/s Takeoff Speed = 127 ft/s 29 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Carpet Plot 30 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Carpet Plot 31 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Weights and Balance Josh Mason 32 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS C. G. Location (1) (2) (3) (4) (5) (6) (7) (8) Fuselage: 63 ft Forward Wing: 67 ft Aft Wing: 93 ft Vertical Tail: 118 ft Engines/Nacelle: 98 ft Landing Gear: 74 ft Fuel System: 62 ft Battery: 16 ft (4) (3) (1) (8) Aircraft: • Forward C. G. Location: 65 ft • Aft C. G. Location: 71 ft (7) (2) (6) (5) 33 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Landing Gear Positioning Longitudinal Placement: • Fuselage 6 ft above the ground • Resulting 15º potential rotation angle • 93% of weight carried by main gear • Most aft cg is 3 ft in front of main gear Rollover Control: • Aircraft can tilt 27º and not roll over • Landing gear in wings 6 ft from centerline • Wing strike limiting factor (strike at 17º) 34 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Control Systems Pete Krupski 35 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Stability Analysis • Longitudinal Stability – Static Margin Range =. 500 to. 149 • (+6. 4 ft to +1. 9 ft) • where is the mean geometric chord of an aerodynamically equivalent monoplane. • Roll Stability – Dihedral angles: +7. 8º & -7. 5º • Yaw Stability – Wing Sweep +/-35º 36 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Control Surfaces • Elevators Flaps –. 3 b, . 3 c Ailerons • Rudder – Sized for 1 -engine-out at landing • . 3 c rudder with 9º deflection • Ailerons –. 3 b, . 3 c • Elevons Elevators –. 3 b, . 5 c 37 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Financial Analysis Joshua Dias 38 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Program Costs • Fixed Costs: – RDT&E = $6. 2 B – Production Tooling = $250 M • TOTAL FIXED COSTS = $6. 45 B 39 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Unit Costs • Price Per Unit = $51 M • COGS = – Materials = $35 M – Production = $10. 8 M • Contribution Per Unit = $16 M • Break-Even: 6 Years ( ~ 400 units) • Net Present Value of PROFIT = $53 B (2008 USD) 40 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Future Considerations • Airfoil – – • • Continue to develop/refine airfoil Optimum Twist on both wings CFD analysis of control surface More study on the interactions at joints Wind Tunnel Testing Work with regulatory agencies regarding remote operator Production Processes (Methods Engineering) Detail Design Marketing Customer-Specific Seating Full-Scale Mock-Up & Egress Testing COMPANY CONFIDENTIAL 41

SCHOOL OF AERONAUTICS AND ASTRONAUTICS References • • • • “Now That’s a Reliable Engine…” July 17, 2006. http: //www. cfm 56. com/index. php? level 2=blog_viewpost&t=75 Boeing Current Market Outlook 2007 “The Airplane that Never Sleeps” July 15, 2002. http: //www. boeing. com/commercial/news/feature/737 qc. html “DC-3 Commercial Transport” http: //www. boeing. com/history/mdc/dc-3. htm “Aerospace Sourcebook”, Aviation. Week & Space Technology, Jan 2007 “Aerospace Sourcebook”, Aviation. Week & Space Technology, Jan 2008 Raymer, D. P. “Aircraft Design: A Conceptual Approach” AIAA 2006 Roskam, J. , “Airplane Design Parts I-VIII”, DARCorporation, KS, 1994 -2007 Bureau of Transportation Statistics, http: //www. bts. gov Bureau of Labor Statistics, http: //www. bls. gov Martin, F. J. , “Green Freedom™ Overview”, Los Alamos National Laboratory, NM, 2007. R. Onishi, Mitsubishi Research Institute, Tokyo, Japan “Flying Ocean Giant: A Multi-Fuselage Concept for Ultra-Large Flying Boat” AIAA-2004 -696 42 nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, Jan. 5 -8, 2004 Wolkovitch, J. (ACA Industries, Inc. , Torrance, CA), “The Joined Wing: An Overview” Journal of Aircraft 1986. 0021 -8669 vol. 23 no. 3 (161 -178) Smith, Stephen C. & Stonum, Ronald K. “Experimental Aerodynamic Characteristics of a Joined. Wing Research Aircraft Configuration. ” NASA Technological Memorandum 101083. April 1989. NASA Ames Research Center. 42 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Thank you! • Questions? – – – – Major Design Requirements Market Analysis Design Mission Materials and Structures Propulsion Sizing Reliability Layout Aerodynamics Weight and Balance Control Systems Financial Analysis Future Considerations 43 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Backup Slides 44 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Mission Weights and C. G. Travel Max Takeoff Weight (MTOW): 70, 700 lbs (add max fuel) Max Flight Weight (MFW): 65, 1000 lbs (add PAX, cargo, and fuel reserves) Max Zero Fuel Weight (MZFW): 60, 000 lbs (add crew) No PAX, 100% Fuel: 46, 700 lbs No PAX, 25% fuel: 40, 000 lbs Operating Empty Weight: 36, 000 lbs Manufacturer’s Empty Weight (MEW): 35, 500 lbs (add trapped fuel and oil) 45 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Constraint Diagram 46 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Back Up Slides ~ Aero~ 47 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Full Flaps CLmax Theory • C 5 Galaxy – Clean CLmax= 1. 45* – Double Slotted Flaps/slats – CLmax= 3. 8* • Optoprime – Clean CLmax= 1. 7 – Triple Slotted Fowler Flaps/ Krugar Flap + Future Technology – CLmax = 4. 9 48 COMPANY CONFIDENTIAL

SCHOOL OF AERONAUTICS AND ASTRONAUTICS Sizing for TO • Used Raymer, Aircraft Design: A conceptual Approach Ch. 5, Fig 5. 4 and Eq. 5. 9 – Jet (W/S) = TOP * sigma* CLTO * (T/W)TO – (100 lbs/ft 2) = 65 *. 835963 * CLTO * (. 4) – CLTO = 4. 5 49 COMPANY CONFIDENTIAL