G.O.D.I.S Complex: “Gaurdian of Defense, Intelligence & Surveillance” Project Advisor: Dr. James...
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Transcript of G.O.D.I.S Complex: “Gaurdian of Defense, Intelligence & Surveillance” Project Advisor: Dr. James...
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G.O.D.I.S Complex:“Gaurdian of Defense, Intelligence & Surveillance”
Project Advisor: Dr. James Lang
Team Leader: Dan Dalton
Chief Engineer: Eugene Mahmoud
Propulsion Specialist: Caitlin Smythe
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Motivation:Northrop Grumman-Bird of Prey
U.S. Patent:5984231 June 19th, 1998
Image from: www.area51zone.com
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Outline of Presentation
• Mission Profiles & Prioritization
• Preliminary Vehicle Configurations
• Downselect Criteria
• GODIS Configuration
• GODIS Performance
• Aerodynamics, Stability & Control
• Engine Integration
• Weights & Sub-systems
• Cost and Supportability
• Conclusion
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Mission #1
Mission #2
Mission Profiles
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Mission #5
Mission #4
Mission #3
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Mission PrioritiesMission #1
Mission #2
Mission #4
With Fallouts:
Mission #3
Mission #5
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Vehicle ConfigurationsConfiguration #1
Endurance/Performance
Configuration #3High-Speed Fighter
Configuration #2High-Altitude Bomber
Configuration #4Dolphin
Configuration #5Low-Altitude Bomber
Configuration #6Crowd Control
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JLFANG Concepts:Endurance/Performance (Config. #1)
High-Speed Fighter (Config. #2)High-Altitude Bomber (Config #3)
Preliminary Researchon Supersonic Performance
and High-Technology
Mission 5:De-prioritized Comparative Study
Conducted to DetermineMissions Prioritization
and Optimal Compatibility
Mission Priorities:Counter Air
& High-AltitudeInterdiction
G.O.D.I.S COMPLEX
“Gaurdian of Defense,Intelligence, and Surveillance”
Subsonic UAV Concepts: Dolphin (Config. #4),
Low Alt. Bomber (Config #5),Crowd Control (Config #6)
Significant Factors in Design
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GODIS configuration
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Maneuver Weight Performance(G.O.D.I.S. Complex alpha @ 0.9 Mach, 15000 feet)
• Max. Mach Number @ Military Thrust = 1.61M• Specific Excess Thrust:
1-g Max. Thrust = 903 feet/sec 5-g Max. Thrust = 674 feet/sec
• Maximum Sustained Turn = 15.73 deg/sec• Maximum Sustained Loading = 9.0+• Max. Instantaneous Turn Rate = 20.64 deg/sec
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0
10
20
30
40
50
60
70
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8
Mach Number
Alt
itu
de
(103
fee
t)
1-g Cl Max Ps=100 Ps=300 Ps=500 Q Max Ps=700 Ps=1000
1-g Specific Excess Power(G.O.D.I.S Complex alpha at Maneuver Weight)
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Aerodynamics
• Area = 760 ft2
• Aspect Ratio = 5.45
• Sweep angle (L.E.) = -28° (extended), 50° (swept)
• Taper Ratio = 0.14 (extended), 0.05 (swept)
• t/c = 0.14 (extended), 0.04 (swept)
• Wing Root : NACA 64210.68
• Wing Tip : NACA 64209.80
• L/Dmax subsonic = 15
• CL,max subsonic = 1.43
• CDo subsonic = 0.016
• Mcrit = 0.88
Mach number vs K
-0.050
0.050.1
0.150.2
0.250.3
0.350.4
0 0.5 1 1.5 2
Mach number
K M vs K
Mach number vs Parasitic drag
00.0050.01
0.0150.02
0.0250.03
0.0350.04
0 0.5 1 1.5
Mach number
CDo M vs Cdo
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Aerodynamics (continued)
• Canard (control)– NACA 65A009 airfoil
– 50 degree sweep
– taper ratio = 0.4
– aspect ratio = 4
• Control Surfaces– subsonic: 2 flaperons per wing:
• First: (near tip) chord = 5.0 ft; span = 19.3 ft
• Second: (closer to root) chord = 5.7 ft; span = 16.1 ft
– supersonic: 2 flaperons on rear:• chord = 4.8 ft
• span = 6 ft
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Stability & Control
• Due to variable forward swept wings, Switchblade requires an active flight control system (AFCS)
– Switchblade will have “relaxed static stability” (i.e. - a negative static margin)
• The AFCS will maintain center of gravity (c.g.) positioning as well as canard, flaperon, and thrust vectoring interaction to achieve unparalleled performance regardless of mission type
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Engine IntegrationTwo engines per module
• Missions 1, 2 & 4
– Afterburning turbofan
– Tmax (s.l.) = 45886 lb*
– Dmax = 3.63 ft*
• Missions 3 & 5
– High-Bypass Turbofan
– Tmax (s.l.) = 17030 lb*
– Dmax = 2.37 ft*
• External compression 2-D ramp with 3-shock inlet
– Diffuser Length = 19 ft*
– External Length = 2.1 ft*
• 3-D Thrust Vectoring Nozzle
– Exit Area = 4.35 ft *
* per engine, nozzle, or inlet
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Weight Estimates & Center of Gravity Travel
C. G. Travel
Counter Air Missions/High-Altitude Interdiction: Complex alphaPropulsion: Afterburning Low Bypass Turbofan EngineEmpty Weight = 37,675 lbsInternal Payload = 4,000 lbsInternal Fuel = 26,730 lbsMaximum Mach number = 1.6Maximum Thrust = 91,663 lbs Engine Weight = 9,959 lbs (2)
Maritime Strike/ISR-Attack: Complex betaPropulsion: High Bypass Turbofan EngineEmpty Weight = 32,410.5 lbsInternal Payload = 4,000 lbsInternal Fuel = 25,830 lbsMaximum Mach number = 1.1 Maximum Thrust = 34,061 lbs Engine Weight = 3,918 lbs (2)
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Cost and Supportability
• Flyaway + RDT&E
planes produced FA+RDT&E (per airplane)
50 $190 million 100 $120 million
500 $51 million
• Lifecycle Costs
planes produced Total LCC 50 $17 billion
500 $33 billion
Supportability
modular engines
variable sweep
engine height
thrust vectoring system
Cost
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Conclusion: Future Work Needed
• Aerodynamics
• Center of Gravity Travel
• Stability and Controls
• Inlet Configuration & Propulsion System
• Subsystem Weights and Cost
• Sustained Loading
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