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.

• 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。