Objectives:

  1. Validate wing spar analysis code
  2. Test wing joining method
  3. Develop procedure for wing construction

Test Article

Screenshot 2024-08-19 123600.png

Screenshot 2024-08-24 091954.png

Screenshot 2024-08-24 092057.png

Screenshot 2024-08-24 095156.png

mkgs
b 3.44
j 1.15
d_r 0.02486
d_1 0.02013
d_t 0.01166
m_0 4.53
t 0.00008
s_crit 6*10^8
N 10
w_int 0.05
g 9.81

Sizing Output

WT1_Shear&Moment.png

WT1_CapLayup.png

Test Data

Foam Core Dimensions (mm):

Should Be Actual Delta (%)
Root Chord: 226 213 -6.1
Root Thickness: 24.9 23.5 -6.0
Mid Chord 183 170 -7.6
Mid Thickness 20.1 18 -11.7
Tip Chord 115 106 -8.5
Tip Thickness 11.7 11 -6.4

AVG Chord $\Delta$: -7.4%

AVG Thickness $\Delta$: -8.0%

Screenshot 2024-08-19 124303.png

*Revised CAD: