This paper investigates ablation mechanism from experimental and theoretical aspects.
本文从实验和理论两方面对小口径固冲发动机补燃室绝热层的传热烧蚀机理进行了研究。
参考来源 - 炮射固体火箭冲压发动机绝热层传热烧蚀性能研究This dissertation researches ablation phenomena of hypersonic projectile. Firstly, the complete research is acted to its ablation phenomenon and ablation mechanism.
本文以超高速飞行的弹箭为研究对象，首先对其表面的烧蚀现象和烧蚀机理进行了全面而深入的研究。
参考来源 - 超高速弹箭表面气动烧蚀规律研究及其对外弹道特性的影响分析·2,447,543篇论文数据，部分数据来源于NoteExpress
The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
本文研究了碳-酚醛材料在固体火箭发动机喷管中的烧蚀机理及性能。
The results show that the experimental system can be used for simulation of oxygen-rich condition, so that selection of insulation formula and ablation mechanism investigation can be carried out.
结果表明，该系统能够模拟富氧烧蚀环境，可利用该试验方法开展富氧环境下绝热层配方筛选和烧蚀机理研究。
The formulas to compute the charred thickness are derived based on its ablation mechanism and the methods to determine its design thickness arc given based on thermal protection for the chamber case.
根据内绝热层的烧蚀机理，推导出内绝热层炭优厚度计算公式；根据燃烧室壳体对热防护的要求，给出了确定内绝热层设计厚度的方法。
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