Multi-span structures with internal supports are widely used in the aircraft industry.Due to the strong abilities of energy absorption, heat insulation as well as noise reduction, lattice sandwich structures have attracted more and more scientists attention.Therefore, in this investigation, the aerothermoelastic properties of multi-span panels with lattice sandwich cores are studied.The nonlinear effects caused by the geometrical large deformation are taken into account.Since the panel studied here is thin, the classical laminated plate theory is applied.