Thermal-Mechanical Optimization of Folded Core Sandwich Panels for Thermal Protection Systems of Space Vehicles

Table 6

Comparison of predicted results with FEM results.

Case	(K)		(kg/m^2)
RBF	423	0.008	36.29
FEM	423.36	0.00804	36.32
Error (%)	0.085	0.498	0.083
RBF	423	0.01	35.07
FEM	423.49	0.00962	35.05
Error (%)	0.116	3.950	0.057