飞航导弹/涡扇发动机一体化设计-约束分析与任务分析

1引言与火箭发动机相比,涡喷、涡扇发动机在亚声速条件下具有更高的比冲,而且发动机的状态可以调节,因而推力可以改变,所以以涡喷、涡扇发动机为主动力的飞航导弹具有更远的射程,并能够实现更为复杂的飞行弹道。另一方面,由于涡喷、涡扇发动机的特性参数(推力和耗油率)会随飞行

Maneuverable missile and turbofan engine integrated design-constrain analysis and mission analysis

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.