Sky By OceanAire Outline - PowerPoint Presentation

Sky By OceanAire

Outline Mission Statement and Assumptions Business Plan Concepts of Operations Requirements Technologies and Advance Concepts Initial Sizing

Mission Statement Design an aircraft with supersonic capabilities that is able to link major business city pairs. C ompete with other existing aircraft on the market.

Assumptions For this design we will assume first flight in 2020 and entry in service in 2023. This will allow us to consider the integration of technologies under development and have a more competitive product. W e assume that no supersonic flight over land is permitted. This allows us the reduce the risks taken by launching an aircraft designed to fly overland if the regulations of prohibited supersonic operations don't change.

Business Plan: Customer Needs and Benefits Decrease travel time by at least half Fly farther non-stop Luxurious cabin space

Business Plan: Primary Customer Business oriented travelers Traveler with the desire and means to reach their destination faster

Business Plan: Market Size According to Richard Branson, founder and President of Virgin Atlantic, “There clearly is a demand for a niche for an all-business-class offering” Eos, MAXjet , Silverjet , and l’Avion reported in 2007 that each filled 70% or more of their seats flying only transatlantic flights.

Business Plan: Market Competition By the year 2020, many companies will be developing or already have developed supersonic transports Table 1. 2020 Market Analysis Company Name # of PAX Range (nmi) Cruise Speed (Mach #) Over Land Aerion Corporation SBJ 8 to 12 >4000 1.6 Yes Lockheed QSST up to 12 >4000 1.6 to 1.8 Yes Dassault Aviation HISAC 8 to 16 3000-4900 1.8 Yes Sukhoi S-21 6 to 10 2400 1.4 N/A OceanAire 49 5000 1.8 No Sky

Business Plan: Market Competition Our aircraft’s strengths are passenger capacity (49), range capability (5000 nmi), and supersonic cruise speed (1.8). Our weakness is that our plane will not be designed for transcontinental flights. Per FAR36, supersonic overland flight in the USA as well as over 50 other countries has been prohibited. Our competition rely on this regulation to be redefined or using new technological advances to mitigate the sonic boom level.

Business Plan: Cost Predictions   Analysis based on Aircraft Airframe Cost Model, using planes that are in production as skeleton models.   We (lbs) Max Speed (mph) # of Test Planes Production Quantity Sell Price (millions) CALCULATOR (Millions) 2004 2009 PROFIT (Million) QSST 80071 1190 2 350 80 66 70.6 3290 Aerion 45139 1058 2 300 80 41.5 44.4 10680 OceanAire 96359 1322 2 325 120 86 91.2 9360 Table 2. Cost Predictions

Business Plan: Operations Up until today, supersonic overland flight in the United States as well as in over 50 countries has been prohibited. Many projects worldwide, like HISAC, strive at on one hand mitigating the sonic boom level through different technical means, and on the other hand, defining what could be the acceptable level of sonic boom for overflown population. A total of 15 city pairs and 13 global locations   Airport Code Airport Code Distance (nmi) LA to Tokyo LAX NRT 4737 SF to Tokyo SFO NRT 4462 SF to Seoul SFO ICN 4927 Seattle to Tokyo SEA NRT 4144 Seattle to Seoul SEA ICN 4533 Tokyo to Singapore NRT SIN >4211 Tokyo to Sydney NRT SYD 2889   Airport Code Airport Code Distance (nmi) NYC to London JFK LHR 2999 NYC to Paris JFK CDG 3158 NYC to Amsterdam JFK AMS 3166 Boston to London BOS LHR 2837Boston to ParisBOSCDG2997Boston to AmsterdamBOS AMS 3004 Miami to London MIA LHR 3845 Miami to Paris MIA CDG 3987 Table 3. Transpacific City Pairs Table 4. Transatlantic City Pairs

Up until today, supersonic overland flight in the United States as well as in over 50 countries has been prohibited. Many projects worldwide, like HISAC, strive at on one hand mitigating the sonic boom level through different technical means, and on the other hand, defining what could be the acceptable level of sonic boom for overflown population. Out of all the city pairs, the most passengers are in the 2500 - 3000 nmi range with  about 68,800 passengers/week for 2008. In this range the busiest city pair is London (LHR) to New York (JFK) with about 23,400 passengers a week. Business Plan: Operations Figure 1. Passengers Per Week for Chosen City Pairs

= 60 ” Customers needs Luxurious cabin s pace 1 st Class Seat Pitch = 60” Business Class Seat Pitch = 50” (these configurations are subject to change) Luxurious entertainment and communication capabilities for improved productivity during flight Shorter travel time

Aircraft Payload / Passenger Capacity: Spacing Efficiency Optimizing passenger capacities within designated aircraft spacing to enable maximum profit. To allow effective use of space without inhibiting the comfort of passengers. To maximize profit by avoiding needless use of space. Enhance Flight Efficiency Through optimization of the aircraft payload by avoiding unnecessary payloads (limiting passenger checking baggage to 1x50 lbs since majority of passengers are business oriented and statistically, they do not carry a lot of luggage)

4 Crew Members  180 lbs/crew Baggage  30 lbs/crew 49 Passengers  180 lbs/passenger Baggage  50 lbs/passenger On Board Baggage  15 lbs/passenger X 49 X 4 W = 12005 lbs payload W = 840 lbs crew Aircraft Payload / Passenger Capacity:

Cabin Layout Business Class Seat pitch 50” Seat width 24” Aisle width 20” First Class Seat pitch 60” Seat width 30” Aisle width 30” Figure 2. Cabin Layout

Based on the longest flight of the aircraft in worst case scenario. Follows FAA part 25 regulations for transport aircraft with 2 engines or more. Includes emergency maneuvers such as take off or go around with one inoperative engine. All supersonic legs of the flights are over sea. Aircraft Design Mission Profile

Design Mission Profile

Design Mission Profile

Design Mission Profile

Design Mission Profile A Taxi (9min) B Accelerate to V LO ≥ 1.1∙V S and liftoff with one engine inoperative C Take off to 35ft at V TO ≥ 1.2 ∙ V S with one engine inoperative, gears down at a rate ≥ 2.4%. D Climb to 1,500ft at V CL ≥ 1.25 ∙ V S with one engine inoperative, gears up at a rate ≥ 1.2% E Climb to 10,000 ft at 250 KCAS with all engines operating, gears up at a rate >3% F Accelerate to climb speed G Climb to best cruise altitude at best climb rate H Step cruise for best range (4,919 nmi with head winds) at M = 1.8 A-B C D E F G H I J K L M N O P Q R

I Descend to 10,000 ft J Decelerate to 250 KCAS K Descend to 1,500 ft and loiter for 30 min L Approach at V A ≥ 1.3 ∙ V s M Missed approach, climb at V CL ≤ 1.5 ∙ V s at a rate ≥ 2.1% with one engine inoperative, gears up OR Missed landing, climb at V CL ≤ 1.3 ∙ V s at a rate ≥ 3.2% with all engines operating, gears down) N Cruise for best range (200 nmi alternate airport) with one engine inoperative O Loiter (30 min) P Descend to 1,500 ft Q Approach at V A ≥ 1.3 ∙ V s R Land over a 50ft obstacle at V TD ≥ 1.15 ∙ Vs Design Mission Profile A-B C D E F G H I J K L M N O P Q R

Economic Mission Profile Based on the most flown flight Follows FAA part 25 regulations for transport aircraft climb rates Does NOT include emergency maneuvers All supersonic legs of the flights are over sea.

Economic Mission Profile A Taxi (9min) B Accelerate to V LO ≥ 1.1 ∙ V S and liftoff with all engines operating C Take off to 35ft at V TO ≥ 1.1 ∙ V s with all engine operating, gear down at a rate > 0% D Climb to 1,500ft at V CL ≥ 1.2 ∙ V s with all engines operating, gear up at a rate > 3% E Climb to 10,000 ft at 250 KCAS with all engines operating, gear up at a rate > 3% F Accelerate to climb speed G Climb to best cruise altitude at best climb rate H Step cruise for best range A-B C D E F G H I J K L M N H Step cruise for best range (3,000 nmi) I Descend to 10,000ft J Decelerate to 250 KCAS K Descend to 1,500ft L 30 min loiter at 1,500ft M Approach at V A ≥ 1.3 ∙ V s N Land over a 50ft obstacle at V TD ≥ 1.15 ∙ V s O Taxi to gate (9 min)

Purdue University is an Equal Opportunity/Equal Access institution. Economic Mission Profile

Purdue University is an Equal Opportunity/Equal Access institution. Economic Mission Profile

Economic Mission Profile

Customer Needs/Wants Airline Passenger Public NASA/Lockheed Airport compatible Maintenance cost Operational life Turnaround time Oversea Range Comfort Cargo space/payload Fast trip time Affordable ticket price FAA requirements Quiet Low emissions Supersonic cruise efficiency Low sonic boom High lift for takeoff and landing Table 5. Customer Attributes

 Quantifiable Engineering Characteristics  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 NO x emissions

 House of Quality Most Important Attributes: 1. FAA Requirements 2. Supersonic Cruise Efficiency 3. Airport Compatible Top Engineering Characteristics: 1. Cruise Mach Number 2. Cruise efficiency

Targets/Thresholds Requirements Compliance Matrix   Requirement Unit Condition Target Threshold Design Date Takeoff Field Length [ft] < 10,000 11,800 11000 1/25/2009 Range [nmi] > 5000 4000 3500 Payload [pax] > 49 35 49 Cruise Mach # [N/A] > 1.8 1.6 1.8 Cruise Efficiency [lb fuel/pax-nmi] < 0.25 0.33 0.36 Certification Noise [PldB] < 50 70 69 Cabin Volume per Pax [ft^3/pax] > 11 9.7 8 1/27/2009 Cruise Altitude [ft]   50000 60000 0 Aircraft Life [years] > 30 20 28 Aspect Ratio [N/A] < 2 3.86 2.2 1/29/2009 Thrust to Weight Ratio [N/A] > 0.37 0.3 0.3 Wing Loading [N/A] > 125 95 100 Crew [crew] < 3 5 4 Table 6. Requirements Compliance Matrix

 Benchmarking   Major Competitors: Aerospatiale/BAC Concorde Lockheed Martin Quiet Supersonic Transport Aerion Supersonic Business Jet Benchmarking Outcome: Focuses Shortcomings Figure 3. Benchmarking Analysis

 Technologies & Advanced Concepts   Engines Commercial: Pratt and Whitney JT8D-219 Turbofan 21000 lb takeoff thrust Military: Pratt and Whitney F-119 (LM F-22) Twin Spool Augmented Turbofan 35000 lb thrust Pratt and Whitney F-135 (LM F-35 JSF) 40000 lb thrust   Materials Carbon Fiber Reinforce Plastics (CFRP) : Very strong and lightweight Tensile strength can reach 820,000 psi 2024-T3 Al – 70,000 psi 7075-T6 Al – 83,000 psi Unlimited lifetime if protected and maintained correctly Boeing 787: over 50% carbon fiber material Nanotechnology: Possibility of much lighter and stronger materials by 2020

 Technologies & Advanced Concepts   Wing Configurations Reversed Delta Wing Natural laminar flow 2D flow Nonplanar Wing Configurations: Reduction in induced drag Increase in L/D Canards Increases stability and lift Current Industry Configurations Low AR Aft-fuselage Compression Lift   Fuel Biofuels Cut down on NOx emissions Virgin Atlantic 747 flight

Estimates of L/D Nicolai/ Corke L/D Estimates M < 1: (L/D) max ≈ 1.4 * AR +7.1 M ≥ 1: (L/D) max ≈ 11*Mc-0.5For assumed AR of 2.2 from historical data M < 1: (L/D)max ≈ 10.2AR assumed from Aerion, Concorde, and Tupolev TU-144 M ≥ 1: (L/D) max ≈ 8.2 M C = 1.8 due to specifications Supersonic: ( L/D) cruise ≈ 7.1 Assuming (L/D) cruise ≈ 0.86 (L/D)max

W e/W 0 Predictor Altered Prof. Crossley’s Database We/W0 = bW0c1ARc2(T/W0)c3(W0/S)c4 M max c5 T/W 0 = 0.3 W 0 /S = 100 M max = 2.0W e/W0 = 2.808524W0-0.08453959AR0.1377132 (T/W0) 0.1351319 (W0/S) 0.1789255Mmax0.01676361 We/W0 = 0.413 Table 7. Sizing Database

W e /W 0 Predictor (cont’d) MATLAB code for W e /W0

W e /W 0 Predictor (cont’d) Table 8. Empty Weight Fraction

W e /W 0 Predictor (cont’d) Technology Used Composites Used on more than 50% of plane We/W0,comp = 0.95*We/W02 Engine configurationReduces Weight, SS cruise without afterburner by 2020Compared to Concorde’s 4 engine configuration

Future Sizing FLOPS NASA Langley Code Very specific inputs and outputs Not worth using yet Too many inputs would be taken from old aircraft Certain info needed that is difficult to look up from old A/C, i.e. hard to make accurate guesses

Summary Luxurious, comfortable, and affordable. First and business class customers for optimal profit. 15 transatlantic and transpacific city pairs. Reasonable empty weight fraction from initial sizing. Design focuses: cruise Mach number and cruise efficiency.

Next Steps Second phase of sizing and design. Utilization of FLOPS Assess different airplane configurations. Trade studies, concept generation, concept selection. Selection of propulsion system. Further investigation of advanced technologies.

Seating Charts (Pitch and Width for Business and First on all airlines) http://www.seatguru.com/charts/business_class.php Airport database (runway lengths, codes, locations...) http://www.world-airport-codes.com/ Market Size http://travel.nytimes.com/2007/07/24/business/24premium.html Seat Pitch http://www.aerospaceweb.org/question/planes/seating/seat-pitch.jpgNASA Dryden fact sheet for Tu-144 http://www.nasa.gov/centers/dryden/news/FactSheets/FS-062-DFRC.htmlAerion Corp-Aerion data http://www.aerioncorp.com/technology USAF XB-70 Factsheet F-14D data http://www.globalsecurity.org/military/systems/aircraft/f-14-specs.htm M.A.T.S http://www.anft.net/f-14/f14-specification.htm References