矢量喷管偏转对发动机推力的影响  

Effects of vector nozzle deflection on engine thrust

作　　者：丁凯锋[1] 王小峰[1] 樊思齐[2] 

机构地区：[1]中国飞行试验研究院,陕西西安710089 [2]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《推进技术》2000年第3期23-25,共3页Journal of Propulsion Technology

摘　　要：建立了轴对称矢量喷管数学模型和带这种矢量喷管的发动机数学模型 ,研究了矢量喷管偏转时引起的发动机推力的变化。研究结果表明 :喷管的有效矢量角与几何矢量角近似成正比 ;喷管偏转角较小时 ,喷管的流量系数及发动机的总推力几乎不随几何矢量角变化 ,喷管偏转角较大时 ,喷管的流量系数及发动机的总推力随着几何矢量角的增大而减小 ;发动机的轴向推力随着几何矢量角的增大而减小 。A mathematical model of engine with axisymmetric vector nozzle was established The effects of vector nozzle deflection on engine thrust were studied using the model The results show that the effective thrust vector angles are approximately linear with the geometric thrust vector angles The discharge coefficient of nozzle and total thrust of engine almost keep constant when deflection angle of the vector nozzle is small and they decrease gradually with the increasement of geometric thrust vectoring angle when deflecting angle of the vector nozzle is big The axi thrust of engine decreases and the side thrust of engine increases with the increasement of geometric thrust vector angle

关 键 词：航空发动机 发动机喷管 可动喷管 推力向量控制 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]