ALTERNATE FUEL SOURCE TRAINER; AVIRIDIS H2

Aviridis H2Senior Capstone DesignParks CollegeSpring 2009 Final Presentation

Nicholas Reder Paul Gucwa

Sean Copenhaver Mathew Janda

Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission

Mission

• Mission Statement

•Current Need

•Mission Profile


Mission Statement

The Aviridis H2’s mission is to provide an inexpensive means for the general

public to pursue flight training. By using an alternate fuel source, the airplane

will not rely on the production of oil and gasoline in the modern era of

skyrocketing oil prices. The Aviridis H2 provides a cheap learning platform for

anyone to pursue the clouds.


Current NeedGeneral Aviation Single Engine Piston Aircraft

13000

14000

15000

16000

17000

18000

19000

20000

21000

22000

23000

1990 1992 1994 1996 1998 2000 2002 2004 2006Year

Ho

urs

Flo

wn

Average Petroleum Fuel Prices Per Year

50

100

150

200

250

300

1990 1992 1994 1996 1998 2000 2002 2004 2006

Year

Co

st (

cen

ts)

•In 1990: 21,883 hours flown

•In 2007: 13,501 hours flown

•38.3 % decrease

•From 2000-2007: Average annual growth is -4.1%

•FAA forecasts an average annual growth from 2008-2025 to be 0.7% for piston aircraft and 6.2% for turbine aircraft.

•People are going away from general aviation


V lift off = 54 knots

Mission Profile

V stall = 45 knots Range = 250 NM

Take off distance over obstacle <1500 ft

V cruise = 90 knots

Duration : 120 min flight time, 60 min reserve

Rate of Climb = 200 ft/NM (FAR)


Propulsion

• Energy Source Tradeoff

•Cost Tradeoff

•Hydrogen Fuel Cell System

•Engine/Fuel Cell/Propeller Data


Energy Source Tradeoff

0.0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

Electricity Fuel Cells NaturalGas

Biofuel Diesel Petroleum H

p/W

0

5

10

15

20

25

30

35

40

45

Electricity Fuel Cells Natural Gas Biofuel Diesel Petroleum

$

Specific Power

Available Chart

Operating Cost Per

Hour


Cost Tradeoff Study

Total Cost After 3000 hrs

0

20000

40000

60000

80000

100000

120000

140000

Elect

ricity

Fuel C

ells

Nat

ural

Gas

Biofu

el

Diese

l

Petro

leum

$

Cost After 3000 hrs

Unit Cost


Fuel Cell System

Proton Exchange Membrane Fuel Cell

- Environmentally Friendly


Hydrogen Storage

Tank Details & Specifications

•CFRP Epoxy•Strength: 79.8 ksi•Density: 0.0578 lb/in3

•Thickness: 1.06 in•Factor of safety: 1.50 •Radius: 23 in•Mass: 405 lb•Volume: 30 ft3

•Pressure: 5000 psi


Powerplant Specifications

9.5Length (in)

16Diameter (in)

190Weight (lbs)

74Continuous Power

(Hp)

133Max Power (Hp)

PowerPhase 100Designation

UQM TechnologiesCompany

180Weight (lbs)

2.02Volume (ft^3)

250-380Voltage Range

136Max Power (Hp)

Stack2001Designation

GMCompanyMotor

Fuel Cell


Propeller Sizing

Propeller Sizing

45

50

55

60

65

70

75

0.000 0.200 0.400 0.600 0.800 1.000 1.200

Tip Mach Number

Pro

pel

ler

Dia

met

er (

in)

1500 RPM

2000 RPM

2500 RPM

3000 RPM

3500 RPM

4000 RPM

Ideal Tip Mach Number

Mach Number:0.876Diameter: 64 in

Mach Number: 0.876Diameter: 56 in

• Propeller Sizing based on Tip Mach Number

• Ideally the Mach Number should be around 0.88

• To achieve that Mach Number a diameter of 64 in was chosen

• Advance Ratio J = 0.49


Design & Performance

• Conceptual Design

•Constraint Analysis

•Weights and Balance

•Performance Calculations & Graphs


Conceptual Design Data

0.060HP/W

133HP

2200Max Gross Weight (lbs)

54Hydrogen Fuel (lbs)

50Baggage (lbs)

400Pilot and Passenger (lbs)

1696Empty Weight (lbs)

805Power Plant Weight (lbs)

891Avg Weight W/Out Powerplant

805total:

180Fuel Cell (lbs)

405Hydrogen Fuel Tank (lbs)

30Inverter/Controller (lbs)

190Electric Motor (lbs)

Power Plant Weights


Constraint Analysis

Constraint Analysis

0.0000

0.0100

0.0200

0.0300

0.0400

0.0500

0.0600

0.0700

0.0800

0.0900

0.1000

0 2 4 6 8 10 12 14 16 18 20 22

W/S

HP

/W

Takeoff

Climb

Landing

const speed const alt

DA20

DA40

C150

C152

C172

PA-38

PA-28

TB9

CTLS

Sportstar

Average

AFST

Aviridis H2


Weights & Balance

Moment (in-lbs)

Station (in)

Weight (lbs)Summary*

*All individual component’s stations and moments shown in back-up slides

21707498.672200Takeoff Weight:

799214854Hydrogen

600012050Baggage

1800090200Passenger

1800090200Pilot

16708298.521696Total Empty

Weight:


Performance Calculations

• Key parameters calculated:

1885(Rate of Climb)max (fpm)

70V best range

56V lift off

47V stall

Knots Sea Level Velocities


Drag Polar

Drag vs. Velocity at Sea Level

0

50

100

150

200

250

70 90 110 130 150 170 190 210 230

Velocity (fps)

Dra

g (

lbs

)

Induced Drag

Wing Profile

Fuselage Drag

Empanage and Landing Gear

Interference and Cooling

Total Drag


Stability & Control, Structures

• Control Surface Sizing

•Center of gravity range

•Static & Dynamic Stability

•V-n Diagram


Control Surface Sizing

• Horizontal tail control surface:Selevator = 16 ft2

Celevator = 1.3 ft

Max deflection = + 30o

• Rudder SizingSrudder = 10 ft2

Crudder= 1.5 ft

Max deflection = + 25o

• Aileron Sizing:Saileron = 9.3 ft2

Caileron = .9 ft

Max deflection = +20o , -30o


Stability & Control

• Static Stability

dCm/dCl: -0.079

Cmo = .1– Statically Stable– Stick Fixed Static

Margin = 7.9%– Stick Free Static

Margin = 6.3%

• Dynamic Stability:– Short Period Response:

• ωn = 3.54 rad/sec

• ζ = 2.82– Phugoid Response:

• ωn = .0037 rad/sec

• ζ = -.0769dCm/dCl

-0.15

-0.1

-0.05

0

0.05

0.1

0.15

0 0.5 1 1.5 2 2.5 3

Cl

Cm


Center of Gravity Range

99.1Aft (in aft of datum)

95.5Forward (in aft of datum)

Center of Gravity Range:

lt

N.P.

LwLT

W

DT

Macw

MF

acw

Datum Plane


V-n Diagram

-3.00

-2.00

-1.00

0.00

1.00

2.00

3.00

4.00

5.00

0.00 20.00 40.00 60.00 80.00 100.00 120.00 140.00

V (kts)

n

V-n Diagram

Vstall

47 kts

V maneuver

96 kts VD

130.5 kts

n = 4.4

n = -1.7

Gust Load Factors :

25 fps gust : 2.77

50 fps gust : 2.00


Empennage Structural Analysis

2.69E-02strain_energy

-1.51E+03min_stress_prin (psi)

2.22E+03max_stress_vm (psi)

3.05E-04max_disp_z (in)

5.77E-05max_disp_y (in)

4.30E-05max_disp_x (in)

3.05E-04max_disp_mag (in)

ProMechanica Output


Wing Spar Design

• I – Beam Section– Material: CFRM– Yield Strength: 160 ksi– Dimensions at Root

• Height: 4 in• Width: 4 in• Thickness: .313 in


Model & Wind Tunnel Testing

• Computer Aided Design Model

•Wind Tunnel Model

•Wind Tunnel Data


Computer Aided Design Model


Wind Tunnel Model


Wind Tunnel Data

CL vs. Alpha

-1.5

-1

-0.5

0

0.5

1

1.5

-10 -5 0 5 10 15 20

alpha (deg)

CL Run


Wind Tunnel Data

CD vs. Alpha

0

0.05

0.1

0.15

0.2

0.25

0.3

-10 -5 0 5 10 15 20

alpha (deg)

CD Run


Wind Tunnel Data

CM vs. Alpha

-20

-15

-10

-5

0

5

-10 -5 0 5 10 15 20

alpha

CM Run


Conclusions

• Risk Analysis

•Cost Analysis

•Final Comparisons & Statements


Risk Analysis

33Failures Due to Cold Ambient Temperatures10

52Hydrogen Igniting9

32Hydrogen Leak into Cabin8

41Control Surface Failure7

24Turbulence 6

21Bird Strike5

24Hard Landing4

42High Impact to Hydrogen Tank (Wing)3

33Fuel Cell Failure2

33External Leak of Hydrogen Tank (Wing)1

CONSEQUENCELIKELIHOODRISK#

(1-5)(1-5)

RISK CHART


Risk Analysis Cont.

4, 6

1, 2, 10

8 3 9

5 7

Consequence

1 2 3 4 5

5

4

3 2 1

Lik

elih

ood

Likelihood Consequence

1 Not Likely Minimal or no impact

2 Low Likelihood Minor performance shortfall

3 Likely Moderate Performance shortfall

4 Highly Likely Unacceptable, but workaroundsAvailable

5 Near Certainty Unacceptable, no alternatives exist


Cost Analysis

21.48.31.81.612.7Price per 100 aircraft (million $)

2944001130002500022000175000Unit Price ($)

Aviridis H2SportStarPA-38C152DA20

Aviridis Cost Breakdown

Powerplant

Structures

Fuel Cell

Manufacturing

Landing Gear

Subsystems

Hydrogen Tank


Final Comparisons

180510310204261Duration (Minutes)

273700471477547Range (NM)

90110104107138Normal Cruising Speed

(kts)

4745484945Stall Speed, Landing

(kts)

188510207207151000Rate of Climb SL (fpm)

1275660146212001360Landing Distance, 50 ft

672720144013401640TO Distance over 50 ft

Aviridis H2SportStarPA-38C152DA20


Final Statement

• The Aviridis H2 is a competitive trainer aircraft that allows one to “go green” economically without sacrificing performance.

• It provides the aerospace community with a platform to build off of in the field of alternate fuel source aircrafts.

• We expect this technology to skyrocket from here in the near future.

Questions

Acknowledgments

Krishnaswamy Ravindra PhDSanjay Jayaram PhDGötz Bramesfeld PhD

Lawrence G. BoyerFrank J. Coffey

Sandra Kay Bopp

Extra: Back-up Slides

• Weights and Balance

1680028060Vertical Tail

1820028065Horizontal Tail

1440016090Aft Fuselage

54009060Main Landing Gear

2250090250Wing Assembly

59940148405Hydrogen Tank

1170090130Cabin

12803240Forward Fuselage

14003540Nose Wheel

12806420Avionics

6303518AUX Battery

5253515Condensor

9003030Compressor

900050180Fuel Cell

4501530Controller

228012190Electric Motor

245735Gear Box/Governer

152438Propeller

Moment (inlbs)Station (in)Weight (lbs)Component

Reference Datum: Tip of nose

1680028060Vertical Tail

1820028065Horizontal Tail

1440016090Aft Fuselage

54009060Main Landing Gear

2250090250Wing Assembly

59940148405Hydrogen Tank

1170090130Cabin

12803240Forward Fuselage

14003540Nose Wheel

12806420Avionics

6303518AUX Battery

5253515Condensor

9003030Compressor

900050180Fuel Cell

4501530Controller

228012190Electric Motor

245735Gear Box/Governer

152438Propeller

Moment (inlbs)Station (in)Weight (lbs)Component

Reference Datum: Tip of nose

Moment (inlbs)Station (in)

Weight (lbs)

Moment (inlbs)Station (in)

Weight (lbs)


799214854Hydrogen

600012050Baggage

1800090200Passenger

1800090200Pilot

16708298.521696Total Empty

Weight:


799214854Hydrogen

600012050Baggage

1800090200Passenger

1800090200Pilot

16708298.521696Total Empty

Weight:

Back-up Slides

24Best L/D, SL

68Best Glide Airspeed

70Minimum Drag, SL

Velocity (knots)Description

Drag Decomposition Summary Data

Constraint AnalysisAFST

Constraint Analysis

0.0000

0.0100

0.0200

0.0300

0.0400

0.0500

0.0600

0.0700

0.0800

0.0900

0.1000

0 2 4 6 8 10 12 14 16 18 20 22

W/S

HP

/W

Takeoff

Climb

Landing

const speed const alt

DA20

DA40

C150

C152

C172

PA-38

PA-28

TB9

CTLS

Sportstar

Average

AFST

Mission Breakdown

Energy Remaining = 60

min

Total Flight Time= 120

min

6015Taxi

752Landing

777Approach

845Descent

8911Cruise

10040Maneuver

14011Cruise

15110Cruise Climb

1613Climb Out

1641Takeoff

16515Taxi

Remaining Energy (min)Time (min)

Phase of Flight

Similar Aircraft ComparisonDA20 DA40 HK36 C150 C152 C172 PA-38 PA-28 TB9 CTLS SportStar Average

Max TO Weight (lbs) 1764 2645 1694 1600 1670 2450 1670 2150 2337 1320 1320 1874.55Thrust (hp) 125 180 100 100 110 160 112 150 160 100 100 127.00Useful Load (lbs) 600 890 462 490 520 830 582 949 838 550 591 663.82TO Distance 1280 1175 623 735 725 865 820 1120 1230 295 620 862.55TO Distance over 50 ft 1640 1700 980 1385 1340 1525 1440 1650 1870 1500 720 1431.82Landing Distance, Ground Roll 661 1155 445 475 520 635 625 640 550 590 629.60Landing Distance, 50 ft 1360 2093 1075 1200 1250 1462 1160 1378 967 660 1260.50Rate of Climb SL (fpm) 1000 1120 965 670 715 720 720 660 665 960 1020 837.73Ceiling 13120 16400 14000 14700 13500 13000 14300 12000 14000 15500 14052.00Stall Speed, Landing (kts) 45 49 42 49 43 48 47 50 39 45 45.70Normal Cruising Speed (kts) 138 150 100 107 107 114 104 108 111 112 110 114.64Range (NM) 547 720 366 477 687 471 465 460 1080 700 597.30Endurance (Minutes) 261 300 225 204 228 310.34 300 243 370 510 295.13Engine Dry Weight (lbs) 230 280 140 170.18 207 327 240 277 277 140.6 136 220.43Power/Weight Engine 0.543 0.643 0.714 0.588 0.531 0.489 0.467 0.542 0.578 0.711 0.735 0.59Carburator weight (lbs) 10 10 10 10 10 10 10 10 10 10 10 10.00Empty Weight (lbs) 1164 1755 1232 1110 1150 1620 1088 1201 1499 770 729 1210.73Weight w/o power plant (lbs) 924 1465 1082 929.82 933 1283 838 914 1212 619.4 583 980.29S 125 145 165 160 160 174 125 160 128 107 106 141.36HP / W 0.071 0.068 0.059 0.063 0.066 0.065 0.067 0.070 0.068 0.076 0.076 0.07W / S 14.11 18.24 10.27 10.00 10.44 14.08 13.36 13.44 18.26 12.34 12.45 13.36b (ft) 35.67 39.16 53.50 33.33 33.75 36.00 34.00 30.00 32.67 28.00 28.40 34.95Aspect Ratio 10.18 10.58 17.35 6.94 7.12 7.45 9.25 5.63 8.34 7.33 7.61 8.89

1.8690.001671258000300-420221PowerPhase 125UQM Tech

0.71190.00134100 250-400405PowerPhase 100UQM Tech

1.14987.00010075800025-420240Powerphase 75UQM

0.4012028160.3912000250-380158HydroGen 3GM

0.5441498160.39 250-380185-224HydroGen 1GM

0.6521328664.12300460300Symetron P-2

Raser Technologies

0.69292.56447.722000300170Symetron P-50

Raser Technologies

Power/Weight (Hp/lbs)

Weight (lbs)Hp

Power (kW)

RPM (max torque)Voltage

Max Torque (lbs*ft)

Motor DesignationCompany

Electric Motor Selection

Fuel Cell Selection

0.2440.40113.90466.421285280C902Ballard

0.1190.19201.001694770150550-960B902Ballard

0.7581.24136.68180.482102250-380Stack2001GM

0.6581.08125.96191.48794250-380Stack2000GM

0.1320.2232.16244.211124200DemonstratorBoeing Demonstrator

Power/Weight (Hp/lbs)

Power/Weight (kW/kg)

Power (Hp)

Weight (lbs)

Weight (kg)

Power Rating (kW)VoltageDesignationCompany

Stability & Control

• Wing Lift ContributionCLw: 0.3343

• Tail Lift ContributionCLt: 0.0237

• Total Lift CoefficientCLtotal: 0.3469

• Drag CoefficientCD: 0.0377

ALTERNATE FUEL SOURCE TRAINER; AVIRIDIS H2

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