Based on advanced thermal management method

a novel thermal protection structure was proposed for scramjet combustion chamber. High temperature heat pipe panels were used to decrease the local high temperature by achieving isotherm. Simultaneously

fuel pipes were embedded to achieve active cooling. The performance was analyzed by numerical simulation

and the influences of the design parameters were evaluated. A sample panel was prepared and evaluated by quartz lamp heating test. In typical circumstance

its unit area mass was 35.4% and 38.2% of oxygen-free copper panel and high temperature super alloy panel

respectively. The maximum temperature difference was less than 80K when the maximum temperature was 1123K in the local heating test. As a proposed thermal protection method

the structure can improve the scramjet thermal protection performance compared with the traditional fuel cooling method.