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飞航导弹/涡扇发动机一体化设计-优化设计
引用本文:陈玉春,刘振德,王晓东,史亚红,屠秋野.飞航导弹/涡扇发动机一体化设计-优化设计[J].推进技术,2006,27(4):303-306.
作者姓名:陈玉春  刘振德  王晓东  史亚红  屠秋野
作者单位:1. 西北工业大学,动力与能源学院,陕西,西安,710072
2. 航天科工集团公司31所,北京,100074
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优化设计模型并给出了算例和分析。根据飞航导弹的要求对涡扇发动机进行了循环参数优化选择并预测了未来涡扇发动机的发展趋势。在考虑导弹空重、有效载荷和气动特性的情况下,预测了未来先进飞航导弹的性能。建立的飞航导弹/涡扇发动机一体化优化设计模型还能够用于已有飞航导弹的任务剖面的优化设计,具有很好的工程实用价值。

关 键 词:飞航式导弹  涡轮风扇发动机  一体化设计  优化设计
文章编号:1001-4055(2006)04-0303-04
收稿时间:2005-09-20
修稿时间:2006-01-27

Maneuverable missile and turbofan engine integrated design-design optimization
CHEN Yu-chun,LIU Zhen-de,WANG Xiao-dong,SHI Ya-hong and TU Qiuye.Maneuverable missile and turbofan engine integrated design-design optimization[J].Journal of Propulsion Technology,2006,27(4):303-306.
Authors:CHEN Yu-chun  LIU Zhen-de  WANG Xiao-dong  SHI Ya-hong and TU Qiuye
Abstract:By using the method of aircraft and turbofan engine integrated analysis, a model of maneuverable missile and turbofan engine integrated optimum design was developed and the computational examples and the analysis were presented. The cycle parameters of missile for turbofan engine were optimized for meeting the demand of maneuverable missile, and the developing trend of missile for turbofan engine was predicted. The performance of next generation maneuverable missile was predicted by taking into account its important parameters such as lift to drag ratio, empty weight to total weight ratio and effective load. The model can be also used for mission section optimization.
Keywords:Aerodynamic missile  Turbofan engine  Integrated design  Optimum design
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