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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. Motivation: Northrop Grumman-Bird of Prey. U.S. Patent: 5984231. June 19th, 1998. - PowerPoint PPT Presentation
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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
Motivation:Northrop Grumman-Bird of Prey
U.S. Patent:5984231 June 19th, 1998
Image from: www.area51zone.com
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
Mission #1
Mission #2
Mission Profiles
Mission #5
Mission #4
Mission #3
Mission PrioritiesMission #1
Mission #2
Mission #4
With Fallouts:
Mission #3
Mission #5
Vehicle ConfigurationsConfiguration #1
Endurance/Performance
Configuration #3High-Speed Fighter
Configuration #2High-Altitude Bomber
Configuration #4Dolphin
Configuration #5Low-Altitude Bomber
Configuration #6Crowd Control
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
GODIS configuration
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
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)
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
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
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
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
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)
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
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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