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

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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

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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

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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

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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