42nd AIAA Aerospace Sciences Meeting

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Raytheon Aircraft CompanySupersonic Civil
Aircraft Study
Sponsored Under NASA Langley Contract L-71387D
42nd AIAA Aerospace Sciences Meeting Meeting
Societys Needs with Supersonic
Transportation 05 January, 2004
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Outline

• Introduction
• Study Objectives
• Requirements Definition
• Configuration Synthesis
• Technology
• Market Assessments
• Summary

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Program Objectives

• Four QSBJ objectives for current study
• Develop design requirements for a small
  supersonic aircraft.
• Develop two conceptual configurations designed to
  meet the requirements, with the key
  differentiator being the reduced boom level for
  one of the vehicles
• Determine the technology suite required for
  these vehicles
• Perform a cost and marketability assessment of
  these vehicles

Requirements
Conceptual Designs
Technology
Cost Marketability
One year contract during 2003 Fiscal Year
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Design Requirements Summary
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Design Process
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Design Process

• Four aircraft considered in preliminary design
• Low-boom Tailed
• Low-boom Tail-less
• High-boom Tailed
• High-boom Tail-less
• Class I analysis conducted on all configurations
• Volume, weight and balance
• Cruise L/D
• Field Performance
• Sonic Boom
• Downselect to one low-boom and one high-boom
  configuration at end of Class I analysis

Tail-less configurations chosen for both designs
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Low-Boom Configuration
Wing Area 2743 ft2 AR 1.74 OB LE. Sweep
60 Oper.. Empty Wt. 49,180 lb Payload 1,200
lb Fuel 68,820 lb TOGW 119,200 lb
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High-Boom Configuration
Wing Area 1770 ft2 AR 2.24 OB LE. Sweep
60 Oper.. Empty Wt. 42,240 lb Payload 1,200
lb Fuel 57,920 lb TOGW 101,360 lb
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ConfigurationBasic Characteristics
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Performance Summary
All performance requirements are met for Low-Boom
and High-Boom
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Sizing ThumbprintLow Boom
VLOF145 kts
MTOW 122,000
121,000
VLOF155 kts
120,000
119,000
Optimum 118,300
BFL 5500
118,000
3-view 119,200
BFL 6000
117,000
BFL 6500
VLOF165 kts
BFL 7000
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Sizing ThumbprintHigh Boom
VLOF145 kts
MTOW 105,000
VLOF155 kts
104,000
103,000
3-view 101,360
102,000
Optimum 101,050
101,000
BFL 5500
100,000
BFL 6000
VLOF165 kts
BFL 6500
BFL 7000
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Fuselage Volume Utilization
High Boom
CRUISE CG
ENGINE ACCESSORIES APU
FUEL
FUEL
CABIN
MAIN GEAR
CREW STA
HYD ELEC
NLG
BAG
WIRE HARNESS, DUCTS, ETC.
CRUISE CG
Low Boom
ENGINE ACCESSORIES APU
CABIN
FUEL
FUEL
BAG
MAIN GEAR
CREW STA
HYD ELEC
NLG
WIRE HARNESS, DUCTS, ETC.
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Sonic Boom SuppressionRequirement Satisfied
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Airport Noise

• Airport noise was a significant design driver
• Engine size / weight / cycle
• Impacts to distribution of volume and
  consequently boom and wave drag
• GE worked the noise issue diligently
• ACE engine concept
• End result surprisingly good
• 21 db margin to Stage 3
• 11 db margin to assumed Stage 4

Stage 4 Airport Noise requirement is satisfied
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Structural Layout

• Fuselage
• Composite construction
• Fwd Fuselage sections
• Cabin section (Pressure vessel)
• Mid Fuselage section (Fuel sections)
• Inlet ducts
• Nacelle outer shells
• Metallic
• Keels
• Landing gear
• Nacelle Torque Box

• Wing
• Metallic Components
• Attach fittings to
• Leading edge surfaces
• Wing box carry-through structure
• Outboard skin sections
• Tip section

• Wing - Composite Components
• Spars, Inboard ribs
• Control surfaces (full depth core)
• Skin panel construction

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Systems Layout

• AIRCRAFT SYSTEMS
• External Vision
• Anti-Ice System
• Air Data Measuring
• Avionics
• Pressurization
• Environmental Control
• Emergency Oxygen
• More-Electric-Aircraft
• Hydraulics
• Auxiliary Power
• Fuel Management
• Flight Controls

No significant differences between low-boom and
high-boom systems
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Cabin Layout

• Aft-Fuselage entry door
• Emergency Egress between club seats

• Lavatory and galley located in aft-cabin
• Advanced cockpit in forward cabin with external
  vision system

Double-Club seat arrangement seats 8 passengers
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Technology Requirements
Systems
Propulsion
Noise
Low Speed
Weight
Efficient A/F
Emissions
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Pareto Analysis on Technology Needs
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Technology Challenges

• The six highest ranked Technology Challenges are
• Reducing Noise Footprint (including sonic boom)
• Propulsion Power Efficiency
• Efficient Airframe (high cruise L/D)
• Structural Systems Weight
• Advanced Vehicle Systems
• Low Speed Performance

Assumed certification and entry into service at
end of year 2013
Technology roadmaps were produced for all
critical technology areas
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Cost Analysis

• Increased cost when designing for low-boom
  depends on
• Design Impacts
• Increased aircraft length
• Controlled equivalent area distribution
• Critical placement of engines
• Development program impacts
• Operational considerations
• Impact on Society

Program cost estimated for each configuration to
quantify differences
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Marketability

• Marketability relates to utility for the Customer
• Time
• Avoids delays associated with hub and spoke
  airline routing
• Customer sets own flight schedule not the
  airlines
• Less time is spent on ground security,
  check-in, etc
• Access
• Customer can fly directly into the preferred
  airfield nearest their destination
• Marketing usually focuses on more concrete
  variables Range, speed, field length, etc.

Customers justify the acquisition of a business
jet by the UTILITY it brings. The common
denominator is TIME.
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MarketabilityAirport Access

• Study highlighted the distinction between a
  field length requirement and an airport
  access requirement
• Corporate aircraft operators view field length
  today as the sole enabler for operation into
  their airports of interest
• Their true requirement is not a field length,
  per se, but access to certain airports
• Resulting weight for current QSBJ configurations
  became a blocker at many high traffic GA
  airports

Airport access must be addressed for QSBJ success
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Marketability Direct Operating Cost

• Direct operating costs slightly higher than
  subsonic
• Supersonic flight over land will result in time
  savings that offset increased operating costs

Value of passengers time will determine utility
of aircraft
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MarketabilitySupersonic Flight Over Land

• With restrictions on supersonic flight over land

• Range of aircraft is decreased below design point
• Average speed is decreased ? Longer mission
  duration
• Operating costs increase
• Utility to customer limited
• Business case is challenged

Definition of regulatory requirements to allow
supersonic flight over land is imperative
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Summary

• Two parallel designs were created
• One constrained by boom, the other not
• All other requirements the same
• Closure on all requirements
• Sonic boom
• Airport noise
• Performance
• Critical technologies were identified
• Roadmaps developed
• Marketability
• Cost of low-boom higher, but yields
  significantly more utility

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The World is Small...
When You Fly A