This paper is focused on a probabilistic design of the honeycomb structure which is a constituent unit of satellite. The design is considering launching and space environments by kriging metamodel. The proposed methodology using the kriging metamodel is conducted by stochastic step-moving method (SSMM) as the criterion of a sequential approximate optimization to satisfy the global optimum value based on the local optimum value. Also, Design of Experiments (DOE) is used to reduce computation costs. The honeycomb structure is analyzed for reliability. For the optimal design, constraints are taken for natural frequency and several stresses that should be considered on the satellite platform in launching situations. Thermal effects of space environments and wrinkling are also considered since a structural sandwich is often poor at carrying in-plane compressive loads and may be inflicted with instability and thermal effect.