参考飞航导弹/涡扇发动机一体化设计的思路,建立了基于能量法的反辐射导弹/固体推进剂空气涡轮火箭发动机(SPATR,solidpropellantairturborocket)总体性能计算的约束分析和任务分析模型并给出相应的算例和分析。简述了空射反辐射导弹任务剖面、约束条件的给定、导弹的重量组成以及SPATR发动机模型。计算结果表明,相比采用固体火箭发动机的HARM导弹,采用SPATR发动机的反辐射导弹具有超音速飞行(H=11km,2.5Ma;H=3km,1.8Ma)、远航程(低、高空航程均增加47%以上)和盘旋待机(H=3km,0.6Ma,300s)能力,其性能极具使用价值。

By using the method of maneuverable missile and turbofan engine integrated analysis, a constrain and mission analysis model of anti-radiation missile and SPATR's overall performance calculation was developed and the competitive examples and the analysis were given. The mission section, the constrain conditions, the weight composition of the anti-radiation missile and the model used in SPATR were presented. Compared with anti-radiation missile with solid rocket, constrain analysis results and the mission analysis results of some anti-radiation missiles indicate that anti-radiation missiles with SPATR have supersonic flight capacity (H=11km, 2.5Ma, H=3km, 1. 8Ma), a farther missile flight range capacity (greater than 47%), hovering and standby capacity (H=3km, 0.6Ma,300s), whose performance has well application value.