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对具有大后翼装药结构的Φ315 mm发动机和全尺寸发动机进行了地面点火试验。试验后对喷管收敛段绝热层按照沟槽和非沟槽部位进行了解剖,得出了各个部位绝热层的烧蚀和炭化数据。结果表明,和药柱翼槽对应的喷管收敛段绝热层烧蚀严重,而非药柱翼槽对应部位的绝热层烧蚀较小。实测的最大烧蚀率可用于同类发动机的方案设计。
Surface ignition tests were conducted on a Φ315 mm engine with a large rear wing charge and a full-size engine. After the test, the heat insulation layer of the convergent section of the nozzle was dissected according to the groove and the non-groove parts, and the ablation and carbonization data of the heat insulation layers of all the parts were obtained. The results show that the ablation of the heat insulation layer of nozzle convergence section corresponding to the wing column of the medicine column is serious, while the heat insulation layer ablation of the corresponding part of the wing column of non-medicine column is smaller. Measured maximum ablation rate can be used for similar engine design.