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大后翼装药固体发动机喷管收敛段绝热层烧蚀
Ablation of nozzle convergent section insulation of solid rocket motors with long aft-finocyl grain
【摘要】 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。
【Abstract】 The ground firing tests of Φ315 mm motor and full-scale motor with long aft finocyl grain were performed.The nozzle convergent section insulation was dissected respectively according to groove section and non-groove section.The depth of ablation and charring layers was obtained.The results show that the ablation of the nozzle convergent section insulation corresponding grain fin-slots is high and the ablation corresponding grain non-fin-slots is low.The maximum ablation rate measured may be applied to design of the same kind of motors.
【关键词】 固体推进剂火箭发动机;
点火试验;
烧蚀;
装药;
绝热层;
【Key words】 Solid propellant rocket engine; Ignition test; Ablation; Charge; Heat insulation layer;
【Key words】 Solid propellant rocket engine; Ignition test; Ablation; Charge; Heat insulation layer;
- 【文献出处】 推进技术 ,Journal of Propulsion Technology , 编辑部邮箱 ,2009年01期
- 【分类号】V435
- 【被引频次】1
- 【下载频次】195