Assembling and Supporting the Joint Strike Fighter in the UK
Inventing the Joint Strike Fighter - aereo.jor.br
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Inventing the Joint Strike Fighter Dr. Paul Bevilaqua Lockheed Martin Skunk Works
Transcript of Inventing the Joint Strike Fighter - aereo.jor.br
Inventing the Joint Strike Fighter
Dr. Paul BevilaquaLockheed Martin Skunk Works
General Arrangement
Length 50 ft
Span 35 ft
Wing area 450 sq ft
Empty Weight 30,000 lbs
AB Thrust 40,000 lbs
Vertical Lift 40,000 lbs
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Relative Size of Naval JSF
JSF1018010
Length 51 ftSpan 43 ftWing Area 620 ftInternal Fuel 19,500 lbSpot Factor 1.09
Length 47 ftSpan 30 ftWing Area 240 ftInternal Fuel 7,900 lbSpot Factor .82
Length 56 ftSpan 37 ftWing Area 400 ftInternal Fuel 10,800 lbSpot factor 1.0
2 2 2
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Service Needs
• USMC 609− STOVL Strike Fighter to Replace
the AV-8B and F/A-18C/D
• RN and RAF 150− Supersonic STOVL Replacement
for the Sea Harrier and GR-7
• USAF 1763− Stealthy Strike Fighter to
Replace the F-16 and A-10
• USN 480− Stealthy Strike Fighter
3000 US/UK Joint Strike Fighters
DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited.DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
JSF Family of Aircraft
Length 51 ftSpan 43 ftWing Area 620 ft2
Internal fuel 19,500 lbs
Naval
Length 50 ftSpan 35 ftWing Area 460 ft2
Internal fuel 13,250 lbs
STOVL
Length 50 ftSpan 35 ftWing Area 460 ft2
Internal fuel 18,500 lbs
CTOL
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
JSF Commonality
Cousin Parts
Designed for Self Defense
360o Visibility
AESA Long Range Radar
Twin Verticals
High T/ W
Low Span Loading
Low W / S
High CL max
2 Internal AIM 120’s
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Designed for Ground Attack
Low IR Signature
Internal Precision Guided WeaponsAgile
Stable Target Tracking
Good Field of View
Low Vulnerability
Supersonic SpeedsInternal EO Systems
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Designed for Low Vulnerability
Hot Parts Aft
Fuel Tank Inerting
Multiple Fuel Tanks
Pilot Protection
Dry Bay Fire Protection
Jettisonable Weapons
Multiple Load Paths
Redundant Control Surfaces
Air Start System
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Designed for Maintainability
Integrated Subsystems
Auxiliary Power UnitOn Board Diagnostics
Advanced Cockpit
Self Contained Ladder
OBOGS
OBIGGS
Benign Footprint
Single Point Systems Check
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
F-16C
F/A-18C
Sustained G’s
USAF
USMC/RN
USN
ADVANTAGE
Transonic Acceleration
F-16C
USMC/RN
USN
USAF
F/A-18C
Air to Air Combat Performance
F-16C
F/A-18C
USAF
USMC/RN
Instantaneous G’s
USN
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Naval F-35C Mission Performance
730 w/ TanksMission Radius - nm 600
USN Profile: (2) 2K lb JDAM + (2) AIM-120
Opt M/Alt Cruise
FLOT
400 nm
Combat @ 35K ft
Drop A-G Weapons
JSF 768
F/A-18C 329
927 2x 480 galTanks
547 3x 330 galTanks
DISTRIBUTION STATEMENT For Official Use Only
USMC F-35B Mission Performance
Mission Radius - nm
USMC Interdiction B: (2) 1K lb JDAM + (2) AIM-120
50 nm
Opt M/Alt CruiseIngress• 540 KTAS/15,000 ft
FLOT
/Egress
Drop A-G Weapons
550 w/ Tanks450
JSF 473 663 2x 480 galTanks
F/A-18C 375Lot XIX w/ (2)1K JDAM+(2)AIM-120+(5)Pylons + Gun
AV-8B 273
2x 330 galTanks504
DISTRIBUTION STATEMENT For Official Use Only
How We Won: The X - Planes
“Lockheed won by proposing a very innovative lift fan” - Boeing
“Lift Fan Puts LockMart over the Top” - Aviation Week
“Lift Fan Carries LM to Victory” - Interavia
Lift Fan Propulsion System
Lift Fan
ClutchFan Drive Shaft
Roll Control Jets
Thrust Vectoring Nozzle
Cruise Engine
AV-8 Harrier Adopted by US Marine Corps1970
The Harrier Approach Isn’t Supersonic
F-104 Starfighter
15,000 lbs Thrust
Mach 2
AV-8B Harrier
20,000 lbs Thrust
M < 1
Design Missions
Requirements AnalysisWilloughby Templates
SEGMENT
NEED
MISSION
VTOL Requirement Sizes the Engine
VTOL Design Point
CTOLDesign
Point
Sustained Turn Instantaneous Turn
TransonicAcceleration
STO
VL
1.2
1.3
1.0
1.1
.8
.9
00 20 30 40 50 60 70 80 90
Wing Loading (WTO / S)
Thrust toWeightRatio
(TSL / WTO )
Engine Requirements Analysis
Segment
Need
Feature
ShortTake Off
WingLift
JetLift
VectorThrust
JetFlap
HighT/W
SubsonicCruise
LowSFC
Combat
MixedFlow
HighT/W
LowIR
LowBPR
LowDrag
HighTSP
LowSFC
VariableBypass Ratio
HighBPR
AftNozzle
VerticalLanding
ReactionControl
HighT/W
LowHGI
Balance ColdJets
SupersonicAcceleration
ThrustTransfer
HighBPR
The Basic Problem: Not Enough Thrust, and It’s Too Far Aft
Weight, 30K lbs
Thrust, 20K lbs
Goal
Weight, 30K lbs
Thrust, 18K lbs Thrust, 18K lbs
Conventional F-16
“V/STOL” F-16
Weight, 30K lbs
Thrust, 18K lbs Thrust, 18K lbs
Solving the Basic ProblemNot Enough Thrust, and It’s Too Far Aft
Means toExtract Power
• Turbines• Scoops• Regeneration• Heat Pipes• Alternator• Generator • MHD• EFD
Means toTransfer Power
• Shafts• Ducts• Heat Pipes • Laser Beams• Chain Drive• Fiber Optics• Wires• Hydraulics
Means toProduce Thrust
• Fans• Rockets• Pulse Jets • Ram Jets• Ejectors• Explosions• MHD• EFD
Shaft Driven Lift Fan Propulsion Concept
JSF119-611 Engine
JSF0419013
Shaft Driven Lift Fan Propulsion Concept
JSF119-611 Engine
JSF0419013
F-35 Propulsion System
JSF119-611 Engine
JSF0419013
Turboshaft EngineProvides Shaft Power, but no Cruise Thrust
Turbofan EngineProvides Cruise Thrust, but no Shaft Power
Alternative Types of Turbine Engine
Extracting Shaft Power
.
Open
Closed
Comparison with LM Lift/Cruise Systemat 40,000 lbs of thrust
0
2000
4000
6000
8000
10000
12000
14000
SDLF DL
Engine
Weight (lbs)
RCS
Inlet
Systems
Nozzle
Lift Fan
Engine
Design Options
Number of Alternative Aircraft Is Too Large
Horizontal Stabilizer Assessment
Lift Fan Installation
JSF STOVL Propulsion System
AV-8B Harrier and the F-35 Musketeer
Fan AugmentationHot Gases AftContinuous Thrust VectoringLift Improvement DevicesPoor Supersonic Area DistributionOvertemp Reduces Engine LifeWater Injection RequiredSide by Side Jets Permit Hot Gas IngestionCompressor Air for Reaction Control Jets
Fan AugmentationHot Gases Aft
Continuous Thrust VectoringLift Improvement Devices
Good Supersonic Area DistributionNo Reduction of Engine LifeNo Water Injection Required
Tandem Jets Prevent Hot Gas IngestionFan Air for Reaction Control Jets
Lockheed Martin Common Strike Fighter
STOVL
CTOL
TFX: The Challenge of Joint Aircraft
USAF F-111
USN F-14 (F-111N)
Technology Assessment Contracts1993
Lockheed Skunk WorksShaft Driven Lift Fan $40M
McDonnell DouglasGas Driven Lift Fan $35M
Demonstrate propulsion and airframeperformance through ground test
McDonnell Douglas Gas Driven Lift Fan Concept1993
Boeing Lift / Cruise Engine Concept1994
Engine
Nozzle
Lockheed Martin Large Scale Powered Model1995
Lockheed Martin Large Scale Powered ModelNASA Testing
Boeing Large Scale Powered Model1996
JSF Concept Demonstrator Awards1996
Boeing X-32
Lift / Cruise Engine
Lockheed Martin X-35
Shaft Driven Lift Fan
• Mature Technologies to Reduce Risk
• Build Aircraft to Validate Performance
• Refine the Design, as Necessary
JSF01070
• Build Two Aircraft, but Fly All Three Variants
• Fly the Production Configurations
• Demonstrate STOVL Performance and Supersonic Speed
• Prove Handling Qualities and Carrier Suitability
Lockheed Martin Demonstrator Approach
X-35 Commonality
X-35 Number 2
X-35 Number 1
Carrier X-35C
CTOL X-35A
STOVL X-35B
Lockheed Martin Aeronautics Company
Validation by High Fidelity Demonstrators
Presenter
Presentation Notes
Full Scale validation by high fidelity demonstrators CTOL30 Days total test time 27.4 Hours tested 27 Flights Mach 1.05 CV12 weeks total test time 58 Hours tested 73 Flights 252 FLCPs Mach 1.22 STOVL 6 weeks total test time 21.5 Hours tested 39 Flights 17 Vertical takeoffs 27 Vertical Landings 14 Short Takeoffs 6 Short landings 2 X mission flights Mach 1.2
CTOL USAF Variant
• 27 Flights totaling 27.4 Hours over 30 Days• LM, BAE SYSTEMS, MOD, and DOD Pilots Flew the X-35A• “People were stunned” Gen Mike Hough, USMC
Lockheed Martin Aeronautics Company JSF0419027
Conversion to STOVL Variant
JSF0419030
Lockheed Martin Aeronautics Company JSF0419031
• Only Aircraft To Fly Supersonically, Hover, and Land Vertically in the Same Flight
– Major Art Tomassetti, USMC, 20 July 2001• 38 Flights in 21.5 Hours
STOVL USMC / Royal Navy Variant
40,000 lbs of Vertical Lift from Just 4 Nozzles
48%
9%
43%
Lift Jet Characteristics
Infrared Lift Jet Visualization
Naval Variant Over Annapolis
DISTRIBUTION STATEMENT Approved for public release; distribution is unlimited.
Edwards Air Force Base• 38 Flights in 33.2 Hours• Use of a Side Stick Demonstrated• Carrier Approaches Flown
Pax River Naval Air Station• 33 Flights in 18.9 hours• Carrier Landings Simulated• Envelope Expanded to M = 1.2
First X-plane to fly across the US• 2 Flights• 5.9 Flight Hours
JSF STOVL Variants
32,000 lbs of Thrust 40,000 lbs of Thrust
What You See, Is What You Get!
2001 Collier Trophy
Awarded for " the greatest achievementin aeronautics or astronautics in America, demonstrated during the preceding year “ to the F-35 Lift Fan Propulsion System
Joint Strike Fighter - Economies of Scale
F-16 Falcon
AV-8 HarrierF-18 Hornet
A-10 Warthog
USAF 1765
USN 480
USMC 610
UK 150
FMS 3000
Total of 6000 aircraft
Total of $200B
The Netherlands
Italy
Norway
Denmark
Canada
Turkey
U.K.
Australia
United States
International Coalition Investing in JSF
This is a Team Success
