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

Table 5

Comparison of FEM simulation results and experimental results for three-point bending.

Title	Name
	Maximum stress/MPa	Error	Maximum displacement/mm	Error
Sandwich equivalent model	127.3	8.43%	3.71	8.1%
Actual model	122.4	4.26%	3.58	4.3%
Three point bending experiment	117.4	/	3.43	/