中国新一代载人飞船返回舱热控设计优化研究

Research on Thermal Control System Optimization of China New Generation Manned Spacecraft Reentry Capsule

文章针对新一代载人飞船返回舱再入过程气动热环境和返回舱传热特性,建立了气动热环境下返回舱动态耦合传热集总参数模型,能够描述返回舱防热层内侧蜂窝板、舱体、设备和舱内空气间的导热、对流及辐射动态耦合换热过程。文章应用该模型对典型新一代载人飞船返回舱气动热环境下的传热特性进行了分析,提出了防热烧蚀层内侧铝蜂窝板表面包覆多层隔热材料、增强舱外设备与返回舱壁热耦合、降低设备表面红外发射率等返回舱热控优化设计措施。热控优化措施应用于中国新一代载人飞船试验船,并通过首次在轨飞行验证,在近第二宇宙速度返回气动热环境下,返回舱结构、空气、设备等各项温度指标均满足指标要求,验证了返回舱热控设计的合理性。研究结果可为返回式航天器热控系统设计提供参考。

In this paper,the heat transfer characteristics of the re-entry capsule of a new generation manned spacecraft in aero-heating environment is discussed.A dynamic conjugate lumped heat transfer of the re-entry capsule in aero-heating environment is proposed,which can describe the dynamic conjugate heat transfer of heat conduction,convection and radiation among the honeycomb panel,cabin structure,equipment and cabin air in the reentry capsule.The model is applied to analyze the heat transfer characteristics of the re-entry capsule of a new generation manned spacecraft in aero-heating environment,and some optimal design measures for re-entry capsule thermal control system are proposed,such as covering the honeycomb panel inside the thermal ablation layer with multi-layer insulation material,enhancing the thermal coupling between the equipment outside the capsule and the capsule structure and reducing the surface emissivity of the equipment.The thermal control optimization measures have been applied to the new generation manned spacecraft in China,and the first on-orbit flight verification shows that the structure,air,equipment and other temperature indexes of the re-entry capsule meet the requirements in the aero-heating environment near the second cosmic velocity return,which verifies the rationality of the thermal control design of the re-entry capsule.The research results can provide reference for the design of the thermal control system of the re-entry spacecraft.