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

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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

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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