飞航导弹/涡扇发动机一体化设计-优化设计

推进技术 ›› 2006, Vol. 27 ›› Issue (4): 303-306.

飞航导弹/涡扇发动机一体化设计-优化设计

陈玉春,刘振德,王晓东,史亚红,屠秋野

北工业大学动力与能源学院陕西西安710072;航天科工集团公司31所;西;北京100074;航天科工集团公司31所;西;北京100074;航天科工集团公司31所;西;北京100074;北工业大学动力与能源学院陕西西安710072

发布日期:2021-08-15
基金资助:
航天支撑基金资助项目(N4CH0002)

Maneuverable missile and turbofan engine integrated design-design optimization

School of Power and Energy,Northwestern Polytechnical Univ.,Xi’an 710072,China;The 31st Research Inst.of CASIC,Beijing 100074,China;The 31st Research Inst.of CASIC,Beijing 100074,China;The 31st Research Inst.of CASIC,Beijing 100074,China;School of Power and Energy,Northwestern Polytechnical Univ.,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

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

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.

Key words: Aerodynamic missile;Turbofan engine;Integrated design;Optimum design

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.