11
Conceptual Design ReviewConceptual Design Review4/17/074/17/07
Team 1Team 1
John HorstJohn Horst Jared OdleJared Odle Keith FayKeith Fay Boyce DaubyBoyce Dauby
Andrew Andrew KovachKovach
Akshay RajeAkshay Raje Manish HandaManish Handa
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 22
Mission Statement:Mission Statement: The objective is to provide a fixed-wing, The objective is to provide a fixed-wing,
semi-autonomous, long-endurance, semi-autonomous, long-endurance, continuous-area coverage unmanned continuous-area coverage unmanned aerial vehicle to relay communication of aerial vehicle to relay communication of tactical importance for an extended period tactical importance for an extended period of time.of time.
Department of DefenseDepartment of Defense Front-line tactical communication relay Front-line tactical communication relay
to/from warfighterto/from warfighter
Relief Agencies/FEMARelief Agencies/FEMA Front-line tactical communication relay Front-line tactical communication relay
to/from ground first respondersto/from ground first responders
Commercial CustomersCommercial Customers Damaged service locations, scouting of Damaged service locations, scouting of
new telecommunication markets, and new telecommunication markets, and remote locationsremote locations
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 33
CONOPSCONOPS TakeoffTakeoff
Conventional runway takeoff (Autonomous or Conventional runway takeoff (Autonomous or Remote Operation)Remote Operation)
Distance from Takeoff to Coverage AreaDistance from Takeoff to Coverage Area
Transmitting/ReceivingTransmitting/Receiving
Ground Forces Ground Forces UAV UAV Command Station Command Station or other Ground Forcesor other Ground Forces
ControlControl Autonomous with manual backup/mission Autonomous with manual backup/mission
overrideoverride
Remote OperatorsRemote Operators Trained military UAV pilots controlling from Trained military UAV pilots controlling from
Mission Command CenterMission Command Center
Level of ThreatLevel of Threat Design for high threat environmentDesign for high threat environment
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 44
CONOPSCONOPS
http://www.afcea.org/signal/articles/templates/SIGNAL_Article_Template.asp?articleid=507&zoneid=4
Provide continuous area coverage for and extended time Provide continuous area coverage for and extended time periodperiod
Multiple UAVs in systemMultiple UAVs in system
Redundancy by overlapping coverageRedundancy by overlapping coverage
Survivability via electronic countermeasuresSurvivability via electronic countermeasures
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 55
Design RequirementsDesign Requirements
Target Threshold
Endurance 24 hr 14 hr
Range 200 nm 50 nm
Ceiling 30,000 ft MSL 15,000 ft MSL
Takeoff 500 ft 1,000 ft
Landing 500 ft 1,000 ft
Transportation Volume
Fit inside C-130
55’x10’x9’
Fit inside C-5
143’x19’x13.5’
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 66
Communications Communications PayloadPayload AJCN - Adaptive Joint C4ISR NodeAJCN - Adaptive Joint C4ISR Node by BAE Systemsby BAE Systems
Weight 200 – 270 lbs
Power 2 hp
Volume* 6 – 9 ft3
Range (Air-to-Ground)** 55 – 100 nm @ 15,000 ft
Range (Air-to-Air)** 60 nm @ 15,000 ft
*Volume approximated by avionic density: 0.02 – 0.03 ft*Volume approximated by avionic density: 0.02 – 0.03 ft33/lb/lb
**According to available data**According to available data
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 77
Additional PayloadAdditional Payload
Missile Warning/Countermeasures - BAE Missile Warning/Countermeasures - BAE SystemsSystems AN/ALQ-156(V) Warning SystemAN/ALQ-156(V) Warning System
425 Watts of Power425 Watts of Power 50 pounds50 pounds 20.4 × 10.2 × 7.6 in20.4 × 10.2 × 7.6 in
AN/ALE-47 Dispensing SystemAN/ALE-47 Dispensing System Automatic ResponseAutomatic Response Protects Against: Protects Against: Air Interceptor (AI), Anti-Aircraft
Artillery (AAA), and Surface-to-Air Missiles (SAMs) 20 pounds20 pounds Fielded on 1,307 AircraftFielded on 1,307 Aircraft 43.7 x 39.5 x 26.8 in43.7 x 39.5 x 26.8 in
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
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Payload SummaryPayload SummaryIntroduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
MicroPilot - Dayview/NightviewMicroPilot - Dayview/Nightview
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 99
SizingSizingIntroduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
Gross Weight Sensitivity to Performance Parameters
3000
3500
4000
4500
5000
5500
6000
6500
7000
7 9 11 13 15 17 19 21
Wing Loading (lbs/sq ft)
Gro
ss W
eig
ht
(lb
s) T/W=0.16
T/W = 0.19
T/W=0.22
T/W=0.25
T/W=0.28
Custom written sizing code. Attempts are being made with
FLOPs and ACS—results may be available in the report.
Using General Aviation component weight predictions from Raymer.
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1010
SizingSizing Various parameters were held constant Various parameters were held constant
during trade studies and carpet plot during trade studies and carpet plot generationgeneration
L/D 12
Propeller Efficiency 0.8
Specific Fuel Consumption
(cbhp)
0.4 lb/hp-hr (cruise)
0.5 lb/hp-hr (loiter)
Loiter Velocity 80 kts
we/w0 (from UAV database)
Aspect Ratio 10
Λ 0
CLmax 1.8 (Takeoff)
1.6 (Landing)
0.36 0.1600.06W E
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1111
Trade-offsTrade-offs Using sizing code, it was Using sizing code, it was
determined that increasing the determined that increasing the design combat range from 100 design combat range from 100 to 200 nm resulted in an to 200 nm resulted in an increase in gross weight of 100 increase in gross weight of 100 lbs.lbs.
Decreasing endurance from 24 Decreasing endurance from 24 hours to 20 hours saved 500 hours to 20 hours saved 500 lbs.lbs.
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1212
Carpet PlotCarpet Plot
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1313
Aircraft DescriptionAircraft Description
*All dimensions in feet*All dimensions in feet
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1414
Aircraft DescriptionAircraft Description
Camera
Rotax 914AJCN
FuelTanks
RearLanding
Gear
MainLanding
Gear
MissileDefenseSystem
Avionics
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1515
1. Camera1. Camera
2. AJCN2. AJCN
3. Engine Nacelles3. Engine Nacelles
4. Missile Defense4. Missile Defense
5. Fuel Tanks5. Fuel Tanks
6. Avionics6. Avionics
*All dimensions in *All dimensions in feetfeet
1 2
3
4
5
6
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1616
AerodynamicsAerodynamics
NACA 65NACA 6522-415-415 Thick profile allows Thick profile allows
easier structural easier structural layoutlayout
Wide drag bucket Wide drag bucket @ high lift @ high lift coefficientscoefficients Center at 0.4Center at 0.4 Extends to 0.9Extends to 0.9 Aircraft travels Aircraft travels
entire range as entire range as fuel is burned fuel is burned and aircraft and aircraft lightenslightens
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1717
AerodynamicsAerodynamics
Trailing edge flaps on main Trailing edge flaps on main wings.wings. Fowler FlapsFowler Flaps 33% chord ratio33% chord ratio 50% of wing area is covered50% of wing area is covered
Basic drag component Basic drag component buildup using techniques buildup using techniques described in Raymerdescribed in Raymer
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1818
AerodynamicsAerodynamics
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 1919
PerformancePerformance
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2020
Target Threshold Current
Endurance 24 hr 14 hr 20 hr
Combat Radius
200 nm 50 nm 200 nm
Ceiling 30,000 ft MSL 15,000 ft MSL 41,000 ft MSL
Takeoff Ground Roll
500 ft 1,000 ft 750 ft
Landing Ground Roll
500 ft 1,000 ft 490 ft
Loiter Altitude 15,000 ft AGL
Current Gross Weight 3,450 lbs
Stall Speed 49 kts
Maximum Speed 150 kts
Compliance MatrixCompliance MatrixIntroduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2121
Propulsion SystemPropulsion System Variable pitch propellerVariable pitch propeller
In-flight adjustable In-flight adjustable Diameter : 7 ftDiameter : 7 ft Number of blades : 3Number of blades : 3 Advance ratio (J) : 0.482Advance ratio (J) : 0.482 Activity Factor (AF) : 100Activity Factor (AF) : 100 Integrated design lift coefficient (ClIntegrated design lift coefficient (Clii) : ) :
0.3 0.3 Maximum working RPM : 2400Maximum working RPM : 2400
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2222
PropulsionPropulsion System System
*Cruise velocity: 80 knots *Cruise velocity: 80 knots *Propeller Efficiency: 0.81*Propeller Efficiency: 0.81
At 1500 agl and 2400 RPM - Efficiency vs. Velocity
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
0 50 100 150 200 250
Velocity (knots)
Eff
icie
nc
y
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2323
Engine DescriptionEngine Description
Rotax 914 UL Aircraft EngineRotax 914 UL Aircraft Engine 100 HP, with maximum 115 HP for 5 minutes100 HP, with maximum 115 HP for 5 minutes 4-stroke, 4-cylinder , with turbo charger 4-stroke, 4-cylinder , with turbo charger Max RPM 5800Max RPM 5800
Integrated reduction gear i = 2.4Integrated reduction gear i = 2.4 Shaft RPM 2400Shaft RPM 2400
Electric starterElectric starter Electric dual ignition systemElectric dual ignition system
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2424
Material ComparisonMaterial ComparisonIntroduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2525
Selected MaterialsSelected Materials
Internal Structure Internal Structure (wing/tail/body)(wing/tail/body) Aluminum 2024-T3Aluminum 2024-T3
Landing GearLanding Gear Aluminum 7075-T6Aluminum 7075-T6
Aircraft SkinAircraft Skin Aluminum 7075-T6Aluminum 7075-T6
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2626
Internal StructureInternal StructureIntroduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2727
Weight BreakdownWeight Breakdown
1. W1. WCameraCamera
2. W2. WAJCNAJCN
3. W3. WEngineEngine
4. W4. WMissile DefenseMissile Defense
5. W5. WMainGearMainGear
6. W6. WWingWing
7. W7. WFuselageFuselage
8. W8. WFuelFuel
9. W9. WAvionicsAvionics
10. W10. WVertTailVertTail
11. W11. WHorizTailHorizTail
12. W12. WRearGearRearGear
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2828
Weight BreakdownWeight Breakdown
*Moment and location measured from tip of the nose*Moment and location measured from tip of the nose
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 2929
Stability & ControlStability & Control
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 3030
Stability & ControlStability & Control
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 3131
Stability & ControlStability & Control
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 3232
Control Surface SizingControl Surface Sizing
Tail Volume Coefficient Method Tail Volume Coefficient Method Vertical tail – 60 ftVertical tail – 60 ft22
Horizontal tail – 68 ftHorizontal tail – 68 ft22
Statistical ApproximationStatistical Approximation Elevator – 22 ftElevator – 22 ft22
Rudder – 25 ftRudder – 25 ft22
Aileron – 31 ftAileron – 31 ft22
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 3333
CostCost Very hard to estimate per Very hard to estimate per
aircraftaircraft DoD Endurance-Payload model DoD Endurance-Payload model
$1.8 million$1.8 million DoD $1500 / lb empty weight DoD $1500 / lb empty weight
$3.2 million$3.2 million DoD $8000 / lb payload DoD $8000 / lb payload
$2.2 million$2.2 million DAPCA IV model, DAPCA IV model,
$2.7 million (50 aircraft $2.7 million (50 aircraft produced)produced)
Average is $2.5 millionAverage is $2.5 million
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work
AAE 451 - Team 1 - 4/17/07AAE 451 - Team 1 - 4/17/07 3434
Future WorkFuture Work SizingSizing
Update Carpet PlotsUpdate Carpet Plots More Accurate Results from ACS and FLOPSMore Accurate Results from ACS and FLOPS
StructuresStructures More detailed layout and analysisMore detailed layout and analysis
Better cost estimateBetter cost estimate Stability and ControlStability and Control
Lateral StabilityLateral Stability Control surface sizingControl surface sizing DynamicsDynamics Flight control computer definitionFlight control computer definition
More detailed Aerodynamic workMore detailed Aerodynamic work Potential flow analysisPotential flow analysis CFD analysisCFD analysis
Introduction
Mission Analysis
Payload
Sizing
Aircraft Description
Aerodynamics
Performance
Propulsion
Structure
Weights
Stability & Control
Cost
Future Work