摘要
针对C/SiC复合材料在不同温度及压力条件下的氧化机制,基于氧化动力学及化学平衡基本模型,获得了C/SiC材料氧化烧蚀行为的理论模型与计算方法;利用典型地面试验,并与电弧风洞地面试验实测数据进行了对比分析。对于被动氧化时的氧化层厚度演化,该模型主要考虑材料表面氧化膜内非等摩尔扩散特性的影响规律,关注边界层内氧扩散及氧化膜内氧输运的竞争控制机制。对于主动氧化条件下的烧蚀质量损失,该模型考虑了低温条件下的动力学烧蚀和高温平衡,重点分析了碳及碳化硅组元的氧化动力学特性、温度、压力和来流质量流率等主要因素对烧蚀行为的影响规律。
Aiming at the oxidation mechanism of carbon/silicon carbide composites under different temperature and pressure,based on the basic model of oxidation kinetics and chemical equilibrium,the theoretical model and calculation method of oxidation and ablation behavior of carbon/silicon carbide composites are obtained,and the simulation analysis is carried out based on the typical arc wind tunnel test results.For the evolution of oxide layer thickness during passive oxidation,the model mainly considers the influence law of non equimolar diffusion characteristics in the oxide film on the material surface,and pays attention to the competitive control mechanism of oxygen diffusion and oxygen transport in the boundary layer.For the ablation mass loss under active oxidation,the model considers the kinetic ablation and high temperature equilibrium under medium and low temperature conditions,and focuses on the effects of the oxidation kinetic characteristics of carbon and silicon carbide components,temperature,pressure and incoming mass flow rate on the ablation behavior.
作者
汪雷
潘勇
邓代英
徐晓亮
俞继军
Wang Lei;Pan Yong;Deng Dai-ying;Xu Xiao-liang;Yu Ji-jun(Beijing Institute of Astronautical Systems Engineering,Beijing,100076;Science and Technology on Space Physics Laboratory,Beijing,100076;China Academy of Aerospace Aerodynamics,Beijing,100074)
出处
《导弹与航天运载技术》
CSCD
北大核心
2022年第4期92-97,共6页
Missiles and Space Vehicles
