丁羟三组元固体推进剂燃烧工况下氧化锆热障涂层烧蚀与隔热性能分析

Analysis of Ablation and Thermal Insulation Performance of ZrO_2 Thermal Barrier Coating Under Combustion Conditions of Hydroxyl-Terminated Polybutadiene Propellant

开展了丁羟三组元固体推进剂燃烧工况下几种不同工艺的氧化锆热障涂层烧蚀、隔热性能研究。通过正交试验,揭示了氧化锆热障涂层烧蚀、隔热性能影响因素(基体厚度、粘接层种类、面层种类及面层厚度)之间的主次关系,将为后续氧化锆热障涂层应用于固体火箭发动机领域提供了设计依据。

The ahlation and thermal insulation pedormance of ZrO2 thermal barrier coating with several different process under combustion conditions of the hydroxyl-terminated polybntadiene propellant was studied. By tile orthogohal experiment, the primary and seeondary relations between the influence factors （matrix-thickness, adhesive-layer type, surface-layer type and surface-layer thickness）with the ablation and thermal insulation performance of ZrO2 thermal barrier coating were revealed. And the result of this work would provide a design basis for the application of ZrO2 thermal barrier cnatings to the field of solid rocket motors.