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Vehicle Sizing PDR

Utilizing historical data and constraints to estimate the weight of an aircraft, including battery weight fractions and flight phase weight calculations. Implementation of Raymer Method for accurate weight estimation.

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Vehicle Sizing PDR

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  1. Vehicle Sizing PDR AAE 451 Fall 2006 Team Whishy Washy Tung Tran Mark Koch Matt Drodofsky Matt Lossmann Ravi Patel Ki-bom Kim Haris Md Ishak Andrew Martin

  2. Historical Data Cessna 182 Alpha 40 Trainer High King Tech Nitro Airstrike

  3. 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

  4. 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

  5. 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

  6. 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

  7. Weight Estimation

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

  9. Constraints

  10. 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

  11. CLmax Constraint • Historical Data • AAE 451 Aerodynamics Sourcebook • Thin Airfoil Based • NACA 4412 Example

  12. Historical Database • Max CL values from Aerodynamics Sourcebook

  13. Thin Airfoil Theory • NACA 4412 • Naca4geo.m • Sourvort.m

  14. 2-D Cla Cla derived from curve fitting Cl-alpha plot 3-D CLa Total CL Thin Airfoil Theory

  15. Thin Aifoil Theory • Added CL due to flaps 2-D change in alpha max Ratio of flapped area to total wing area Sweep angle of flap hinge

  16. Thin Airfoil Theory • Results • Good Agreement with Historical Data

  17. Constraints • Turn Constraint Equation • Q = rho at S.L • V = Vcr • CDo = .022 • A = 7 • E = .8 • ηp = .6 • N =1/cos(45)

  18. Constraints • Land distance constraint • Sland = 120 ft • CLmax = 1.4

  19. Constraint • Take off • μ = .05 • CDO = .022 • ηp = .6

  20. Constraints • Cruise • Vcr = 130 ft/sec • CDO = .022

  21. Constraints • Stall • Vstall = 30 ft/sec • CLmax = 1.4

  22. Constraints • Climb Constraint • ηp = .6 • Vclimb = 80ft/sec • Climb (gamma) = 35deg • L/D = 10

  23. Aircraft Size • Weight – 5.2103 lbs • Horse power – 1.3 • Wing area – 3.47 ft2

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