Abstract: A thermal structure and thermal match test of a full-scale cabin component was conducted in a 200 MW high temperature combustion-heated tunnel. New test methods were developed for some key techniques like tunnel state adjustment, effect of test medium and long term heat flow measurement. New methods of combustion-heated tunnel operation design and equivalent cold-wall heat-flux correction considering combustion gas effects were applied. Long term heat flow evaluation method was also used to simulated variable heat flux boundary conditions at the same test trajectory. The technology method was applied to a full-scale cabin component test successfully. The experiment results show that the aero-heating environments were exactly simulated and the technique was effective and feasible.