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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
赵昆, 刘沛, 王立武, 林志远
西安航天动力技术研究所 西安 710025
摘要:
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。
关键词:  固体推进剂  丁羟三组元  氧化锆涂层  烧蚀性能  隔热性能
DOI:10.12044/j.issn.1007-2330.2018.02.012
分类号:TB35
基金项目:
Analysis of Ablation and Thermal Insulation Performance of ZrO2 Thermal Barrier Coating Under Combustion Conditions of Hydroxyl-Terminated Polybutadiene Propellant
ZHAO Kun, LIU Pei, WANG Liwu, LIN Zhiyuan
The Institute of Xi'an Aerospace Solid Propulsion Technology, Xi'an 710025
Abstract:
The ablation and thermal insulation performance of ZrO2 thermal barrier coating with several different process under combustion conditions of the hydroxyl-terminated polybutadiene propellant was studied. By the orthogonal experiment, the primary and secondary 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 coatings to the field of solid rocket motors.
Key words:  Solid propellant  Hydroxyl-terminated polybutadiene  ZrO2 thermal barrier coating  Ablation performance  Thermal insulation performance