1. Vehicle Sizing PDR Team “Canard” September 14th, 2006 Team 1:
Dane Batema Benoit Blier
Drew Capps Patricia Roman
Kyle Ryan Audrey Serra
John Tapee Carlos Vergara

2. Overview Preliminary Wing Loading and Power Loading Estimate:
- Equations for each constraint
- Constraint diagram
- Engineering judgment
Preliminary Weight Estimate:
-Method of weight estimation
-Database of historical weight data
Summary
AAE 451 Team 1

3. Constraint Equations
Stall
Cruise (Dash)
Climb
AAE 451 Team 1

4. Power loading (lbf/hp)
TAKEOFF
AAE 451 Team 1

5. STALL CLIMB CRUISE (DASH) CD0 = 0.028 CD0 = 0.024 CD0 = 0.020
CLmax = 1.15
CLmax = 1.25
CLmax = 1.35
(L/D)max = 10
(L/D)max = 12
Design Point (1.2, 4.0)
Power loading (lbf/hp)
Vdash = 90 mph (132 ft/s)
Vstall = 30 ft/s
AAE 451 Team 1

6. Preliminary weight estimate
METHOD
How much energy used in each mission phase
Estimation of the battery weight
Historical data
Intersection W
AAE 451 Team 1

7. Preliminary weight estimate
Estimation of the battery weight :
MISSION SEGMENTS
Takeoff
Climb to 20ft
¼ mile dash (straight level flight)
5 minutes loiter (turning flight)
¼ mile return at the most economical speed (straight level flight)
AAE 451 Team 1

8. Preliminary weight estimate
Estimation of the battery weight :
Takeoff :
Given:
ρB= 2.39e5 Joules/lb
(LiPo chosen for weight)
ηmotor = 0.75
Guess:
Time TO = 5 seconds
W/hp = 4 lb/hp
AAE 451 Team 1

9. Preliminary weight estimate
Estimation of the battery weight :
Climb :
Given:
ρB= 2.39e5 Joules/lb
(LiPo chosen for weight)
ηprop = 0.75
ηmotor = 0.75
γ(climb angle) = 35°
Distance Climb = V Tc = 35 ft
Guess:
L/D climb = 10
Vto = 1.1 Vstall = 33 ft/s γ
20 ft
35 ft
Tc = 1 second
AAE 451 Team 1

10. Preliminary weight estimate
Estimation of the battery weight :
¼ mile dash :
Guess:
L/D dash = 1.5
Given:
ρB= 2.39e5 Joules/lb
(LiPo chosen for weight)
ηprop = 0.75
ηmotor = 0.75
Distance dash = V Td = 1320 ft
AAE 451 Team 1

11. Preliminary weight estimate
Estimation of the battery weight :
5 minutes loiter :
Guess:
Vloiter = 50 ft/s
R = 100 ft
= atan (V²/Rg)
L/D loiter = 10
Given:
ρB= 2.39e5 Joules/lb
(LiPo chosen for weight)
ηprop = 0.75
ηmotor = 0.75
Tloiter = 300 seconds
AAE 451 Team 1

12. AAE 451 Team 1

13. Preliminary weight estimate
Estimation of the battery weight :
¼ mile back :
Guess:
L/D return = 10
Given:
ρB= 2.39e5 Joules/lb
(LiPo chosen for weight)
ηprop = 0.75
ηmotor = 0.75
Distance return = V Tr = 1320 ft
AAE 451 Team 1

14. Preliminary weight estimate
Estimation of the battery weight :
14.94%
0.66%
25.51%
55.06%
3.83%
Climbing phase can be neglected
Wb = 3.5% W and
AAE 451 Team 1

15. AAE 451 Team 1

16. Preliminary weight estimate
Analytical solution :
First guess for W
Calculate : a = W – We and b= Wb + Wp
Calculate : a – b
Iterate until a – b = 0
Find final total weight of the airplane : W = 4.99 lb
AAE 451 Team 1

17. Preliminary weight estimate
Graphic solution :
AAE 451 Team 1

18. Summary Design Point Results Weight Power Loading: 4.0 lbf/hp
Wing Loading: 1.2 lbf/ft2
Weight
Total: 4.99 lbs
Battery: 78.8 g
Results
Wing Area = 4.16 ft2
Horsepower = 1.25 hp
AAE 451 Team 1