Experimental-theoretic simulation was performed on thermal-force loading of large-size carrier rocket dome. The simulation was performed with the aid of dome fragments. Two structural types were studied, which were produced by various manufacturing processes: (1) a sandwich structure with laminated sheets and a honeycomb core and (2) a multiwall structure made of carbon fiber reinforced plastic. Theoretical analysis was performed on the load carrying ability of large-size dome shells. Temperature fields were also studied which arose in structural elements under thermal loads varying with time simulating a cyclogram of a rocket flight after its start. Special experimental test bench was used to confirm the load carrying ability of the fragments of sandwich and multiwall panels under simultaneous force and thermal loading in line with an assigned program. The results of the study enabled one to conclude on the potentials of application of each structure type for aero-space engineering.