1. SAE AERO 2017
Joseph Zongolowicz, Kathy Hansen, Nick Montana, Marquis Ward, Frank Dixon, Thomas Houck, Gerald Short, Zhangsiwen Xiao, Kevin Schesventer, and Coleman Gordon

2. Project Criteria Design, Build, and Fly a Remote Control Aircraft
Aircraft must Take Off in 200 ft and Land in 400 ft
Aircraft must be powered by a 1000w power supply
Aircraft cannot exceed 55 lbs Gross Weight
Aircraft must carry as many Passengers and Luggage as Possible
Flight Conditions
25 mph Cruise
45 lbs Gross Weight

3. Aircraft Configuration
Rib spacing for wing and tail was determined historically
Design Tool Improvements
Updated specifications
Determines minimum shear web thickness
Determine minimum spar cap area
CAD Models have been updated
Since the midterm the outer design has been finalized. The optimum rib spacing was determined to be 8 inches by observing similar models. With the rib spacing determined we were able to use the updated design tool to calculate minimum shear web thickness and spar car area to counter the shear, torsion, and bending forces in the wing. This data was then used to model the internal structure of the wing and tail in CAD.

4. Design Tool-Weight
Weight and Balance
Description
Symbol
Value
Units
Comment
Selected design gross weight
W0 =
44.04
lbf
Target loaded C.G.
xCG0 =
6.50 in
Target empty weight
WE =
11.50
Target empty C.G.
xCGE =
7.00
Gravitational Constant
g =
32.17
ft/s2
Static Margin
xsm =
2.50
Stick-fixed Neutral Point
hn =
8.50
0.50
% WMGC
Component
Weight
Station
Moment
Propeller Assembly
0.19
-0.83
-0.16
lbf-in
Measured
Motor
0.73
1.13
0.82
Cowling
1.25
Historical
Speed Controller
0.28
2.00
0.56
Power Limiter
0.04
0.09
Receiver
0.08
Wing Assembly
6.00
12.00
Tail Assembly
43.00
21.50
Fuselage Assembly
0.35
20.00
Covering
0.34
19.33
6.57
Nose Landing Gear
0.37
1.00
Main Landing Gear
0.75
10.25
7.69
0.00
Battery
1.12
Payload
31.43
8.00
251.41
Mission Profile
Calculated Empty CG
7.21
8.17
58.90
Calculated Gross CG
38.64
8.03
310.30
Here is the weight section of the design tool. This tool allows us to analyze the weight distribution of the plane and its effect.

5. Motor and Propeller Specification
Finished propeller testing for the Power 52 and scorpion motor
Final Selection: Power 52 and 15x6 propeller

6. Fuselage Structure Testing
Static Cargo Bay Stress Test: 49.4 lb +
Dynamic Cargo Bay Stress Test Round 1: Failed

7. Fuselage Structure Testing
Tail Boom Stress Test: 9.5 lb

8. Wing Structure Testing
Completed Torsion Testing
Failure Testing in progress
FEA analysis/comparison in progress

9. Wing Structure Testing
Bending data cannot be used to determine deflection equation
Test results indicated stiffness
New test plan uses symmetric loading of 2015 wing

10. Tail Design Deflection Testing Complete Torsion Testing Complete
Original
Covered Modified
Torsion Testing Complete
Modified
Theoretical Static Testing In Progress

11. Gantt Chart

12. Questions?