Lightweight Design of Solar UAV Wing Structures Based on Sandwich Equivalent Theory

Table 4

Experimental data of 70 mm span.

Sample number	Maximum stress/MPa	Maximum strain	Displacement/mm
A1	125.97	1.14	3.38
A2	114.94	1.22	3.42
A3	122.84	1.22	3.52
B1	118.23	1.1	3.37
B2	114	1.1	3.46
B3	127.36	1.18	3.66
C1	112.83	1.21	3.41
C2	115.64	1.05	3.48
C3	118.33	1.14	3.42
D1	115.37	1.15	3.31
D2	122.72	1.01	3.52
D3	115.23	1.19	3.56
E1	115.83	1.1	3.47
E2	104.74	1.07	3.39
E3	122	1.24	3.42
Average	117.4	1.14	3.43