This study presents the design and testing of a metallic thermal protection system (TPS) for future spaceplane vehicles. A conceptual design of the developed metallic TPS panel consisting of an outer sandwich structure, thermal insulation, inner support brackets, and a base framelike structure was redesigned from the metallic TPS panel developed by NASA. The thermal load was selected from a previous study, which was equivalent to the highest surface temperature of 1050 K. Nine metallic TPS prototype panels and supporting hardware structures made of 304 stainless steel were initially prepared for thermomechanical testing in room conditions. A noncontact thermal–mechanical measurement method was employed to measure full-field temperatures and deformations of the inner base structure and supporting hardware structures. The results indicated that the proposed design satisfied the requirements of temperature and permanent deformation limits. Panel-to-panel gaps showed a significant effect on the temperature rise in the inner base structure. The performance of the prototype proved the feasibility, reusability, and durability of using low-cost 304 stainless steel for TPS structures up to four thermal cycles, and may achieve more in further tests. Results provide valuable data for evaluating designs at the early stage of TPS development and testing in space conditions.

这项研究提出了用于未来航天飞机的金属热保护系统（TPS）的设计和测试。由NASA开发的金属TPS面板重新设计了开发的金属TPS面板的概念设计，该面板由外层夹层结构，隔热材料，内部支撑支架和底部框架状结构组成。热负荷是从先前的研究中选择的，该热负荷等于1050 K的最高表面温度。最初准备了九种金属TPS原型面板和由304不锈钢制成的支撑硬件结构，以便在室温下进行热机械测试。采用非接触式热机械测量方法来测量全场温度以及内部基础结构和支撑硬件结构的变形。结果表明，所提出的设计满足了温度和永久变形极限的要求。面板间的间隙对内部基础结构的温度升高显示出显着影响。原型的性能证明了在多达四个热循环的情况下，将低成本304不锈钢用于TPS结构的可行性，可重复使用性和耐用性，并且在进一步的测试中可能会取得更大的成就。结果为在TPS开发的早期阶段评估设计以及在空间条件下进行测试提供了宝贵的数据。在TPS结构中使用低成本304不锈钢的耐久性和耐久性（最多四个热循环），并且在进一步的测试中可能会获得更多。结果为在TPS开发的早期阶段评估设计以及在空间条件下进行测试提供了宝贵的数据。在TPS结构中使用低成本304不锈钢的耐久性和耐久性（最多四个热循环），并且在进一步的测试中可能会获得更多。结果为在TPS开发的早期阶段评估设计以及在空间条件下进行测试提供了宝贵的数据。