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AAE 451 - Aircraft Senior Design

TEAM IIISumitero (Calvin) Darsono

Charles HagenbushKeith HigdonSeung-il KimMatt Lewis

Matt RichterJeff Tippmann

Alex Zaubi

222

Presentations Outline

1. Mission Statement

2. Business Case and Target Markets

3. Concept of Operations

4. Major Design Requirements

5. Aircraft Concept Selections

6. Components – Camera, Avionics, Fuel Cell

7. Power Plant

8. Aircraft Sizing: Constraint Diagram

9. Conclusion

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Mission Statement

To provide a continuous aerial coverage using an UAS that is small, light, portable

and allows rapid deployment

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• Market

• Military•Surveillance around temporary base

•Forward reconnaissance

• Law enforcement and emergency services•Surveillance in assessing hazardous situations before committing personnel

UAS Providing Continuous Coverage for Small Operations

• Business Case

• Small portable UAS• Rapid deployment and coverage

• Multiple aircraft in system

• Little support equipment

• Product is entire system• # of planes

• Laptops

• Communication equipment

• Visual or IR Sensors

• Storage equipment Evolution XTS – L3 BAI Aerosystems

555

Description of Customer - Military

• Military Highlights

• Deployed with squadron

•Launched from location by hand

•Monitor area of interests around operations, 5-10 mile range

• Recognize vehicles and enemy combatants

•Do not need high resolution of plate numbers, faces

• 2-4 planes

• Design to be transported by backpack, though Humvee will probably be sufficient

Elbit Skylark IV (Israel)

Aerovironment Raven

666

Description of Customer – Law Enforcement

• Law Enforcement Highlights• Deployed with SWAT team

•Launched from location by hand

•Monitor area of interests around operations, 5-10 mile range

• Recognize vehicles, people

•Do not need high resolution of plate numbers, faces

• Chemical Spill/ Radiation Monitor• Search for suspect drug manufacturing

• Monitor hazardous chemical spill/ radiations

• Crowd control• Monitor peaceful protest

• 1-2 to planes

• Designed to be transported in vehicle

Octran SkySeer

Raider Marauder

777

Current Market

Military• As of 2005, over 800 small UA

Systems planned• Over 2500 aircraft

• Market is Growing• Armed Forces to spend $20M a

year for the next 3 years on small UA Systems

• Canada and Great Britain looking to obtain similar systems

Law Enforcement• Ideally, each police station could

have one UAV• “It (UAV) provides several things

that we can't get other ways,” quoted Commander Heal of Los Angeles Sheriff Department

Projected Budget for Procurement of Small UA Systems

0

5

10

15

20

25

05 06 07 08 09

Fiscal Year

Bu

dg

et (

$M)

Small UA Systems (<10 lb Gross Weight)

0200400600800

100012001400

DragonEye

Pointer Buster

Number of Systems

Number of Aircraft

888

Major Design Requirement

• Small and light weight aircraft - limited by hand launch requirement, payload weight

• Endurance – limited by the battery, powerplants

• Range – limited by battery and communication relay, power plant

• Payload Weight – limited camera, lens, avionics

• Power - Fuel cell

• Energy Density depends on the weight of the aircraft.

• Fuel cell will be used due to lower weight and higher energy density available

Parameters   Units

Weight 10 lbs

Endurance 4 hrs

Range  5 miles 

Payload Weight  2  lbs

Weight Fraction 0.4  We/Wo 

Energy Density 350 W-hr /kg 

Aerovironment - Raven

999

Aircraft Concept Selection

1 2

83

Design Considerations 1 2 3 4 5 6 7 8Grip - E E - E - - -Stall Speed + E E E E E E EPropeller Performance - E E E - - - -Crash Worthiness - E - E + - - -Handeling - E + E E + E +View from Sensor E E E + E - - E

5

101010

Aircraft Concept Selection

Hybrid 1

• V-Tail, 2-props

Note: Aircraft is not drawn to scale

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Aircraft Concept Selection

Hybrid 2

• V-Tail, forward prop

Note: Aircraft is not drawn to scale

121212

Payload – Camera Core

Camera• Photon OEM Core IR Camera• 320x240 Long Wavelength• Manufactured by FLIR System• Frame Rate = 30 Hz (320X240)• Autonomous and manual camera

operations• Minimum Power Consumption

~1.5W• Weight (~0.27 lbs)

• Camera Core = 0.21 lbs• Rear Cover = 0.03 lbs• Universal Lens Holder = 0.03

lbs• Dimensions

• 2.0 x 2.0 x 1.8 in

Camera Core of Photon OEM

Photon OEM with Lens

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Payload – Camera Lens

Lens

• Two lens are considered

• Focal Length 35.0mm

• 20o HFoV f/1.4•Weight = 0.194 lbs (including lens mount)

•Total Camera Weight = 0.47 lbs

•Optimum for operations up to 1000 ft

• Focal Length 50.0mm

• 14o HFoV f/2.0•Weight = 0.28 lbs (including lens mount)

•Total Camera Weight = 0.56 lbs

•For operations greater than 1000 ft

Distance (ft)

Dimensions (ft)

Resulting Pixels

2000 7 4 431500 5 4 461000 5 4 30

Focal Length (mm)

Object

OEM Photon with 50.0mm Lens

OEM Photon with 35.0mm Lens

Projected Results Obtained from the Camera

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Avionics

Advanced Miniature UAV Autopilots by Micro Pilots

• MP2128LRC Long Range Communications

• Weight of the chip: 0.06 lbs

• Low Power Requirement = 1 Watt

• Rugged Aluminum Enclosures

• Total Weight = 0.727 lbs

• Range of up to 30 miles

• GPS waypoint navigations with altitude

and airspeed hold

• 3 different modes

• autopilot, manually pilot, emergencydirect servo control

• Hand launch take off mode available

MP2128 Autopilot Chips

MP2128LRC Autopilot with Aluminum Enclosures

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Power– Fuel Cells

Procore Fuel Cell

• Manufactured by Protonex

• High Net Power Output = 50 to 200 Watts

• Output Voltage = 20 to 30 Voltages

• Output Current = 1 to 10 Amperes

• High Energy = 770 W-h

• Weight = 4.4 lbs

• Emission

• Hydrogen and Water

Protonex Procore Fuel Cells

Protonex Procore Inside a Model UAV

161616

Component Weight Summary

Component 35 mm Lens 50 mm Lens

Camera 0.275 lbs 0.275 lbs

Lens 0.470 lbs 0.560 lbs

Avionics 0.727 lbs 0.727 lbs

Fuel Cells 4.41 lbs 4.41 lbs

Total Weight 5.882 lbs 5.972 lbs

Required Weight Fraction (We/Wo)

0.4118 0.4028

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Powerplant - Motors

AXI4120/18 Goldline

• Brushless motor with neodymium magnets

• Manufactured by Model Motors s.r.o , Czech Republic

• RPM/V = 515 RPM/V

• Maximum Efficiency = 86%

• Dimensions = 2 in (d) x 2.2 in

• Suggested Max Aircraft Weight = 11lbs

AXI4120/18 Goldline

181818

Propeller Selection - Takeoff (9000 RPM)

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

50

100

150

200

250

300

P (

wat

t)

Propeller Efficiency vs Power for Several Different Pitch/Diameter Ratios

P/D=0.9

P/D=0.8

P/D=0.7P/D=0.6

P/D=0.5

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

0.5

1

1.5

2

2.5

3

3.5

4

Thr

ust

Propeller Efficiency vs thrust for Several Different Pitch/Diameter Ratios

P/D=0.9

P/D=0.8

P/D=0.7P/D=0.6

P/D=0.5

0 20 40 60 80 100 120 1400

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

V (ft/s)

Propeller Efficiency vs Velocity for Several Different Pitch/Diameter Ratios

P/D=0.9

P/D=0.8

P/D=0.7P/D=0.6

P/D=0.5

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Propeller Selection - Cruise (7000 RPM)

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

20

40

60

80

100

120

140

P (

wat

t)

Propeller Efficiency vs Power for Several Different Pitch/Diameter Ratios

P/D=0.9

P/D=0.8

P/D=0.7P/D=0.6

P/D=0.5

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

0.5

1

1.5

2

2.5

Thr

ust

Propeller Efficiency vs thrust for Several Different Pitch/Diameter Ratios

P/D=0.9

P/D=0.8

P/D=0.7P/D=0.6

P/D=0.5

0 20 40 60 80 100 1200

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

V (ft/s)

Propeller Efficiency vs Velocity for Several Different Pitch/Diameter Ratios

P/D=0.9

P/D=0.8

P/D=0.7P/D=0.6

P/D=0.5

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Propeller Selection

• Based off comparison of thrust produced and power required at given speeds.

• Diameter = 10 inchesPitch = 7 inches

• Takeoff

• Velocity: 17 kts

• Efficiency: 50%

• Thrust: 2.3 lbs

• Power: 195 W

• Cruise

• Velocity: 30 kts

• Efficiency: 77%

• Thrust: .9 lbs

• Power: 82 W

Two blades and four blades propellers

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Constraint Diagram

• For the UAV to satisfy the military and law enforcement CONOPS, 5 Constraints will be needed:

• Hand launch take off requirement at 1.1 Vstall (17.22 kts)

• Climb 200 ft/min at 18.8 kts•Climb to 1000 ft at approximately 5 minutes

• Loiter at 30 kts for 4 hours

• Perform a 2-g turn at 30 kts•Turn radius of approximately 12.13 m

• Stall Speed at 15.65 kts (18 mph)

• Basic Assumptions

Parameters   Units

ηp 0.7

Vstall 15.65 kts

VLoiter 30 kts

VClimb 18.8 kts

Climb Rate 200 ft/min

AR 6

CDo 0.02

CLmax 1.3

nmax 2g

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Constraint Diagrams

• The Crucial Limiting Factors:

• 2 g turns – important for maneuverability

• Stall Speed •Important for landing requirements

•Deep stall landing is proposed

• Approximate design point

• Wing loading •1 to 1.1 lb/ft2

•Approximately 10ft2 to 11ft2 of wing area for 10 lbs of aircraft

• Power requirement•15 to 17 watt/lbs

•Approximately 150 to 170 Watts for 10 lbs of aircraft

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Constraint Diagram

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Next Steps

• More on sizing code

• Carpet Plots

• Aerodynamics

• Airfoil Selections

• Aircraft Drag Polar

• Aircraft Performance

• Structures

• Basic structure layout and components placement

• Stability of Control

• Estimations of aircraft c.g

• Estimations of aircraft static margin

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Questions and Comments

ANY QUESTIONS OR COMMENTS?

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Appendix I: CONOPS - Military

Reconnaissance, Security, and Patrol Missions

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Appendix II: QFD

• Two separate scoring for each customer

• Military Customer Important Attributes

• TOGW

• Operative Cost

• Payload Weight

• Number of Aircraft

• Law Enforcement Customer Importance Attributes

• TOGW

• Number of Aircraft

• Acquisition Cost

• Operative Cost

• Payload Weight