| 摘要: |
| 利用飞机/涡扇发动机一体化设计的思路,建立了飞航导弹/涡扇发动机一体化设计的约束分析和任务分析模型并给出了算例和分析。简述了飞航导弹任务剖面、约束条件的给定、导弹的重量组成以及涡扇发动机模型。利用客机/货机升阻特性的预测方法对亚声速飞航导弹的升阻特性进行预测,并给出了合理的修正。利用经验的预测方法对亚声速飞航导弹的空重比进行预测。对飞航导弹的约束分析计算结果和任务分析计算结果表明,建立的飞航导弹/涡扇发动机一体化约束分析与任务分析模型是合理可行的,具有很好的工程实用价值。 |
| 关键词: 飞航式导弹 涡扇发动机 一体化设计 约束分析+ 任务分析+ |
| DOI： |
| 分类号:V235.13 |
| 基金项目:航天支撑基金资助项目(N4CH0002) |
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| Maneuverable missile and turbofan engine integrated design-constrain analysis and mission analysis |
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CHEN Yu-chun,LIU Zhen-de,SHI Ya-hong,TU Qiu-ye,WANG Xiao-dong
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1.School of Power and Energy,Northwestern Polytechnical Univ.,Xi’an 710072,China;2.The 31st Research Inst.of CASIC,Beijing 100074,China
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| Abstract: |
| By using the method of aircraft and turbofan engine integrated analysis,a model of maneuverable missile and turbofan engine integrated constrain analysis and mission analysis was developed and the computative examples and the analysis were given.The mission section,the constrain conditions,the weight composition of the maneuverable missile,and the model of used in turbofan engine maneuverable missile were presented.A prediction method of lift to drag ratio of subsonic maneuverable missile was given.The empty weight to total weight ratio of subsonic maneuverable missile was given experimentally.The constrain-analyzed results and the mission-analyzed results of some maneuverable missiles indicate that the model of maneuverable missile and turbofan integrated constrain analysis and mission analysis is feasible and available. |
| Key words: Aerodynamic missile Turbofan engine Integrated design Constrain analysis~+ Mission analysis~+ |
