Vehicle Sizing PDR

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Vehicle Sizing PDR

AAE 451Fall 2006

Team Whishy Washy

Tung Tran Mark KochMatt Drodofsky Matt Lossmann

Ravi Patel Ki-bom KimHaris Md Ishak Andrew Martin



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Historical Data

Aircraft Model Weight (lbs)

without Payload

Super Cub RTF Electric 1.6245

Cessna 182 1.1325

Alpha 40 Trainer 5.25

Megatech Nitro Airstrike Rc Airplane 5.5

Hign King Tech. model # CTF0026 2.425

Alpha 40 TrainerCessna 182

Nitro AirstrikeHigh King Tech



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Historical Data

• The historical was used to get a approximate estimate of the weight for our models.– The data chosen based on their physical similarities

to our concept– The range is significant because it shows our concept

can easily be adjusted for sizing references



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Weight Estimate

• Raymer Method– Find the weight fractions for different flight phases

• Warm-up - .002• Take off - .02• Climbing - .0002334• Loiter level flight - .0083• Loiter turning flight - .0117• Landing – approximately the same as takeoff



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Weight Estimate

• Combine each phase to determine the battery weight fraction– Validated results with the weight_3.m Matlab file

– Wtot = Wp + We + Wb

– Plot W – We vs. W

– Plot the Historical data vs. W– The historical data trend line is .2103*W+.1243– The battery used was the Lithium Polymer



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Weight Estimation

• Battery– Lithium Polymer

• Volts per cell – 3.7 V• Milliamp hours per cell – 1500 mA• Grams per cell – 36 g• The energy density is 2.517E+05 Joules per lb



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0 1 2 3 4 5 6 7 8 9 100

1

2

3

4

5

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7

8

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Weight~lbf

W-W

e an

d W

b+W

p~lb

f

Estimated aircraft weight is 5.2103 pounds.

Weight estimation using historical weight data

Estimated battery weight is 0.22002 pounds. Payload weight is 1 pound.

Historical data

Estimated weightHistorical data (Foam airplane w/o payload)

Weight Estimation



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Weight Estimation

• The intersection is the estimated weight of the aircraft– W = 5.2013 lbs– The battery weight is .22 lbs



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Constraints



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Constraints• Values Used in Constrain Diagram

– L/D = 10– Climb (gamma) = 35deg

– Vclimb = 80ft/sec

– CLmax = 1.4

– Vstall = 30 ft/sec

– Vcr = 130 ft/sec

– CDO = .022

– Φ = 45 deg

– Sland = 120 ft

– μ = .05

– ηp = .6



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CLmax Constraint

• Historical Data– AAE 451 Aerodynamics Sourcebook

• Thin Airfoil Based– NACA 4412 Example



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Historical Database

• Max CL values from Aerodynamics Sourcebook

CLmax(no flaps) CLmax (flaps)

Gulfstream I ~1.2 ~1.4

SIAI-Marchetti S-211

~1.2 ~1.5

Cessna 310 ~1 ~1.2



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Thin Airfoil Theory

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

•NACA 4412

–Naca4geo.m

–Sourvort.m



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Thin Airfoil Theory

• 2-D Cla– Cla derived from curve

fitting Cl-alpha plot

• 3-D CLa

• Total CLaCLCLeARClCl

CL

1

flapsa CLCLCL



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Thin Aifoil Theory

..

2

..2 cos

lh

f

Da

lhf

Daa

aflaps

S

S

S

S

CLCL

•Added CL due to flaps

Ratio of flapped area to total wing area

Sweep angle of flap hinge

2-D change in alpha max



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Thin Airfoil Theory

• ResultsCla ~7.6

CLa ~5.3

CLflap ~.22

CLmax ~1.2-1.4

•Good Agreement with Historical Data



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Constraints

• Turn Constraint Equation– Q = rho at S.L

– V = Vcr

– CDo = .022

– A = 7– E = .8– ηp = .6

– N =1/cos(45)



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Constraints

• Land distance constraint– Sland = 120 ft

– CLmax = 1.4



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Constraint

• Take off– μ = .05

– CDO = .022

– ηp = .6



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Constraints

• Cruise– Vcr = 130 ft/sec

– CDO = .022



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Constraints

• Stall– Vstall = 30 ft/sec

– CLmax = 1.4



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Constraints

• Climb Constraint– ηp = .6

– Vclimb = 80ft/sec

– Climb (gamma) = 35deg– L/D = 10



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Aircraft Size

• Weight – 5.2103 lbs

• Horse power – 1.3

• Wing area – 3.47 ft2

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Vehicle Sizing PDR

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