1. Vehicle Sizing AAE 451: Team 2 Michael Caldwell Jeff Haddin
Asif Hossain
James Kobyra
John McKinnis
Kathleen Mondino
Andrew Rodenbeck
Jason Tang
Joe Taylor
Tyler Wilhelm

2. Revised Design

3. Modified Mission Objectives
15 minute endurance
Take-off distance less than 60 ft
Vstall less than 15 ft/s
VLoiter less than 25 ft/s
Turn radius of 35 ft
Tabletop defined as 6 ft x 6 ft

4. Constraint Diagram
Modified MATLAB code from Prof. Andrisani AAE 451

5. Mean Chord Investigation
Assumptions
6 ft span, 2.2 lbs aircraft weight
Speeds between 15 and 25 ft/s
Trends
Airfoil CLmax = 1.5
Airfoil CL loiter = 1.0

6. Mean Chord Investigation
12 inch mean chord selected

7. Motor & Propeller Feigao 1208436L Brushless Motor 0.038 lbs
0.472 in. Diameter x 1.22 in. Long
$40
Connected by 0.03 lb :1 Gearbox
Slow Flyer Electric Propeller (EP-1147)
0.022 lbs
11 in. diameter
$1.88
All available at

8. Batteries Two Worley Lithium Polymer batteries 0.10 lbs total
340mAh each
7.4 V each
1.86 x 1.19 x 0.21 in.
$22.99 each

9. Mission Energy Budget

10. Tail Sizing From Raymer’s Aircraft Design: A Conceptual Approach
Horizontal tail (canard) coefficient = 0.3
Vertical tail coefficient = 0.06
Assume tail control surfaces half the total surface area

11. Interior Layout CG AC

12. Stability Analysis Estimation of CG and AC
Distance measured from front of aircraft
CG = ft
AC = ft
Static margin = 16.2%

13. Aircraft Dimensions Wing Main Fuselage Support Fuselages
Wingspan = 72 inches
Mean chord = 12 inches
Main Fuselage
Length = 20 inches
Radius = 2 inches
Support Fuselages
Length = 36 inches
Radius = 1 inch

14. Aerodynamic Surfaces Wing area = 864 in2
Aileron area = in2
Total canard area = in2
Elevator area = in2
Vertical tail area = in2
Rudder area = in2

15. Aircraft Weights Estimated to be 85% foam, 15% balsa
Weight of structure = 1.80 lbs
Weight of batteries = 0.10 lbs
Weight of electronic gear = 0.25 lbs
Weight of motor & prop = 0.06 lbs
Weight of gear box = 0.03 lbs
Total weight = 2.24 lbs

16. Weight Breakdown

17. Immediate Plans Comparison to historical data
Mission specific drag model
Airfoil selection
Trade studies

18. Questions?