alternate fuel source trainer; aviridis h2
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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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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.
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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)
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Propulsion
• Energy Source Tradeoff
•Cost Tradeoff
•Hydrogen Fuel Cell System
•Engine/Fuel Cell/Propeller Data
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Fuel Cell System
Proton Exchange Membrane Fuel Cell
- Environmentally Friendly
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Design & Performance
• Conceptual Design
•Constraint Analysis
•Weights and Balance
•Performance Calculations & Graphs
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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:
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Performance Calculations
• Key parameters calculated:
1885(Rate of Climb)max (fpm)
70V best range
56V lift off
47V stall
Knots Sea Level Velocities
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Stability & Control, Structures
• Control Surface Sizing
•Center of gravity range
•Static & Dynamic Stability
•V-n Diagram
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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 ConclusionsStabilityDesign & PerformancePropulsionMission
Model & Wind Tunnel Testing
• Computer Aided Design Model
•Wind Tunnel Model
•Wind Tunnel Data
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Computer Aided Design Model
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Wind Tunnel Model
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Wind Tunnel Data
CM vs. Alpha
-20
-15
-10
-5
0
5
-10 -5 0 5 10 15 20
alpha
CM Run
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
Conclusions
• Risk Analysis
•Cost Analysis
•Final Comparisons & Statements
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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
Model & Wind Tunnel ConclusionsStabilityDesign & PerformancePropulsionMission
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)
21707498.672200Takeoff Weight:
799214854Hydrogen
600012050Baggage
1800090200Passenger
1800090200Pilot
16708298.521696Total Empty
Weight:
21707498.672200Takeoff 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
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