T eam 2 AAE451 System Requirements Review Chad Carmack Ben - - PowerPoint PPT Presentation

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T eam 2 AAE451 System Requirements Review Chad Carmack Ben - - PowerPoint PPT Presentation

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T eam 2 AAE451 System Requirements Review Chad Carmack Ben Goldman Aaron Martin Russell Hammer Ryan Mayer Donnie Goepper Jake Schaefer Phil Mazurek Abhi Murty John T egah Shane Mooney Chris Simpson Outline Brief Market Overview

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SLIDE 1

T eam 2

AAE451 System Requirements Review

Chad Carmack Aaron Martin Ryan Mayer Jake Schaefer Abhi Murty Shane Mooney Ben Goldman Russell Hammer Donnie Goepper Phil Mazurek John T egah Chris Simpson

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SLIDE 2

Outline

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  • Brief Market Overview

 Customer needs, benefits ,market size and competitors.

  • Concept of Operations

 Customer satisfaction  Flight ranges, runway lengths  Aircraft Payload and passenger capability  Mission Sketch  Segment descriptions

  • System Design Requirements

 Quality Function Deployment(QFD)  NASA N+2 goals  New technology adopted

  • Initial Estimations

 Lift to Drag ratio, Specific Fuel Consumption(SFC)  Empty weight fraction prediction

  • Future Progress

 Project goals and deadlines.

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SLIDE 3

Mission Statement

Designed to maximize productivity and

minimize travel time.

Design an environmentally sensitive business jet

with a wide range of capabilities.

An elite ownership experience awaits

2

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SLIDE 4

Benefits

Time saving capability Long range Comfort and Luxury

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SLIDE 5

Primary Customers

Multinational Corporations Celebrities Governments Fractional Air Services

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“Now more than ever, a business aircraft is an essential tool for capturing new

  • pportunities, for compacting two- to three-

week trips into two to three days. ”

  • Jeff Habib, Senior Vice President of U.S. and

Canadian Sales, Dassault Falcon Jet

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SLIDE 6

Projected Market

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*Source – Honeywell Aviation Forecast The graph indicates that the Long Range market will continue to grow in the next decade.

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SLIDE 7

Jet Purchases

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Big Cabin Jets Captured 40% of Mentions and ~70% of $Value*

*Source – Honeywell Aviation Forecast

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SLIDE 8

Purchase Expectations by Region

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Source – Honeywell Aviation Forecast

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SLIDE 9

Meeting Our Customer’s Needs

 Travel Fast

  • Mach 0.85 Long Range Cruise
  • An Initial Cruise Altitude of 42,000 ft. helps evade

commercial traffic

 Travel Far

  • Maximum Range of 6350 nm
  • LA to Hong Kong, Chicago to Tokyo, non-stop.

 Travel Productively

  • Spacious and comfortable cabin provides a generous

place to both work and relax

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SLIDE 10

Proposed Fuselage

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SLIDE 11

Amenities Dimensions Recliners (10x) – 10 Seats L: 35”, W: 33” Sofas (2x) – 6 Seats L: 90”, W: 35” Tables (3x) L: 24”, W: 35” ConferenceTable L: 36”, W: 60” Lavatories (2x) L: 62” Bar L:62”, W:40” Flight Attendant Seating (2x) – 2 Seats L: 30”, W:30”

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Aircraft Amenities

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SLIDE 12

Amenity Amenity Length Current T

  • tal Length

1 Lavatory 62” x 1 Lavatories 5’ 2” 4 Recliners 35” x 4 Recliners 16’ 10” 1 Tables 24” x 1 Table 18’ 10” 1 Conference Table 38” x 1 Conference Table 22’ 2 Sofas 90” x 2 Sofas 37’ 1 Bar/Kitchenette 72” x 1 Bar/Kitchenette 43’ Miscellaneous Spacing 84” 50’

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Approximating Cabin Length

Amenity Dimensions

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SLIDE 13

Cabin Layout and Dimensions

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SLIDE 14

Fuselage Cross-Section

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SLIDE 15

Total Aircraft Length = (50’ Cabin) + (14’ 2” Nose) + (23’ 10” Tail) = 88’ Cabin Diameter = 8’ 10” Fineness Ratio = 9.96

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Aircraft Characteristics

Volume per passenger (Max. Capacity) = 81.5 cubic feet

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SLIDE 16

Representative City Pairs

 Non-stop possibilities:

  • LA to Seoul

 (5209 nm)

  • Dallas to Moscow

 (5035 nm)

  • LA to Beijing

 (5432 nm)

  • New

York to Dubai  (5949 nm)

  • Chicago to Tokyo

 (5452 nm)

  • LA to Hong Kong

 (6309 nm)

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SLIDE 17

Design Mission

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0-1: Take off to 50 ft. 5-6: Climb to 5000 ft. (Best Rate) 1-2: Climb to 42000 ft. (Best Rate) 6-7: Divert to Alternate 200 nm 2-3: Cruise at Mach 0.85 7-8: 45 minute Holding Pattern 3-4: Decent to Land (No Range Credit) 8-9: Land 4-5: Missed Approach (Go Around) 3 1 2 4 5 6 7 8 9 Takeoff Climb Cruise 6350 nm 200 nm Los Angeles Hong Kong Alternate

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SLIDE 18

Operating Missions

 New

York to Los Angeles

  • Mach 0.9*
  • 2146 nm
  • 16 passengers

 Chicago to Houston

  • Mach 0.9*
  • 804 nm
  • 4 passengers

*Maximum operating Mach dependent on engine selection

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SLIDE 19

Benchmark Aircraft

 Gulfstream G550  Gulfstream G650  Bombardier Global Express

XRS

 Bombardier Global 5000  Gulfstream G500  Citation X  Bombardier Challenger 300  Bombardier Challenger 850  Bombardier Learjet 60 XR  Bombardier Learjet 85  Cessna Citation Sovereign  Gulfstream G150  Hawker 4000  Hawker 750  Hawker 850XP  Hawker 900XP

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SLIDE 20

Fuel Consumption Benchmark

 6.31 lbs/nm (Jane’s All The World’s Aircraft) for

the Gulfstream G650

 3.78 lbs/nm As 40% Reduction Design Goal  Currently the G150 Burns approximately 3.49

lbs/nm

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SLIDE 21

NASA Subsonic Fixed Wing Project

 Develop improved prediction methods and

technologies for lower noise, lower emissions, and higher performance for subsonic aircraft

 Analyzing Research and Testing Methods to

make major improvements by 2020

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SLIDE 22

Advanced T echnology

 Unducted Fan shows promise to reduce emissions and fuel

consumption

 “ERA is focused on the goals of NASA’s N+2, a notional

aircraft with technology primed for development in the 2020 time frame as part of the agency’s subsonic fixed wing program”

  • Aviation Week Dec 14, 2009

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SLIDE 23

Benefits of UDF

 Relative to 1998 levels, NASA plans to reduce

cumulative noise levels to 42 dB below stage 4, 75% lower NOx emissions, and reduce fuel burn by 40%

  • Aviation Week

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SLIDE 24

House of Quality

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SLIDE 25

Requirements Compliance Matrix Part 1

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Performance Characteristics Target Threshold Current Range 6300 nm 6000 nm 6300 nm Takeoff Distance 6000 ft 7000 ft 6000 ft

  • Max. Pax.

17 8 16 Cruise Mach 0.85 0.8 0.85 Cruise Altitude 45000 ft 40000 ft 45000 ft

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SLIDE 26

Requirements Compliance Matrix Part 2

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Performance Characteristics Target Threshold Current Cabin Noise 60 dB 70 dB 65 dB LTO NOx Emissions CAEP 6-75% CAEP 6-60% CAEP 6-70% Cumulative certification noise limits 232 dB 274 dB 274 dB

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SLIDE 27

Requirements Compliance Matrix Part 3

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Performance Characteristics Target Threshold Current Fuel cost per mile 3.8 lb/mile 4 lb/mile 6.23 lb/mile Loading Door Still height 4 ft 5 ft 4 ft Variable Costs $4100/hr $4300/hr $4100/hr

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SLIDE 28

Constraint Diagram

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SLIDE 29

Constraint Diagram Analysis

 T/W limited by Second Segment Climb

  • Current min. is ~0.33

 W/S limited by Landing Ground Roll

(3500ft)

  • Current max. is ~100

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SLIDE 30

Aircraft Database

 Database Includes two classes

  • Class 1: Larger Business Jets

 Gulfstream G500  Gulfstream G550  Gulfstream G650  Bombardier Global 5000

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SLIDE 31

Aircraft Database

 Database Includes two classes

  • Class 2: Smaller Business Jets

 Cessna Citation X  Cessna Citation Sovereign  Bombardier Challenger 300, 850  Bombardier Learjet 60XR, 85  Gulfstream G150  Hawker 750, 850XP, 900XP, 4000

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SLIDE 32

Aircraft Database

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y = 1.378x-0.08 0.45 0.47 0.49 0.51 0.53 0.55 0.57 0.59 0.61 0.63 0.65 20000 40000 60000 80000 100000 120000 We/Wo Wo

T eam 2 Aircraft Database

Class 2: Smaller Planes Class 1: Larger Planes

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SLIDE 33

Performance Estimates

 Aspect Ratio

  • AR = 8.0
  • Estimated from existing Business Jets

 Lift to Drag Ratio at Cruise

  • L/D = 0.85[1.4(AR)+7.1] = 15.56
  • Source: Raymer and Carte

 Specific Fuel Consumptions

  • SFCcruise = 0.5
  • SFCloiter = 0.6
  • Estimated from existing Business Jet engine data

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SLIDE 34

Weight Estimates

 Least Squares Regression: 108,000 lbs

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0.154 0.016 0.394 0.089 0.934 0.032

3.08 ( / ) ( / )

e SL cruise

W W AR T W W S M Range W

1 2 3 4 5 6

( / ) ( / )

c c c c c c e SL cruise

W bW AR T W W S M Range W

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SLIDE 35

Weight Estimates

 Curve Fit with Similar Planes: 92,000 lbs

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y = 67.69x-0.42 0.5 0.51 0.52 0.53 0.54 0.55 0.56 0.57 84000 86000 88000 90000 92000 94000 96000 98000 100000 102000 We/Wo Wo

Similarly Sized Planes

0.422

67.69

c e

W aW W W

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SLIDE 36

Performance Prediction

35 0.7 0.72 0.74 0.76 0.78 0.8 0.82 0.84 0.86 0.88 0.9 5600 5800 6000 6200 6400 6600 6800 7000 7200 Mach Number Range (nmi) Range vs. Mach for Various Loadings 08 Passengers 12 Passengers 16 Passengers

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SLIDE 37

T echnology Factors

 Currently none are being used

  • Predicts “worst case” in early design stage
  • Should make it easier to meet initial design

goals once technology factors are included

 Anticipated T

echnology Factors

  • Empty Weight (composites)
  • Engine Efficiency (unducted turbofan)

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SLIDE 38

Next Steps

 More accurate L/D equations  Inclusion of technology factors in sizing  Development of aircraft performance

code

 Acquiring engine configurations and

performance data

 Choosing wing type and analyzing

aerodynamic data to minimize drag

 Completing aircraft Catia model

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SLIDE 39

Questions?

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