| 1. | The empty weight to total weight ratio of subsonic maneuverable missile was given experimentally
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。 |
| 2. | 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
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。 |
| 3. | 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
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。 |
| 4. | 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
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。 |
| 5. | 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。 |
| 6. | 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
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。 |
| 7. | 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
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。 |
