双喉道推力矢量喷管研究进展  

Research Progress of the Dual-throat Thrust-vectoring Nozzle

作　　者：夏雪峰[1] 高峰[1] 黄桂彬 杨文佳[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《航空工程进展》2017年第3期249-255,298,共8页Advances in Aeronautical Science and Engineering

摘　　要：推力矢量喷管能够大幅提升飞行器的机动性,传统机械式矢量喷管因结构复杂、可靠性差等缺点而使用受限,相比之下,气动矢量喷管的综合性能更为突出,已发展出多种类型,包括激波控制型、双喉道型等。本文简要介绍了气动矢量控制技术的发展现状,重点综述了矢量效果最好的双喉道喷管在二元、轴对称模型气动特性和构型优化等方面的研究情况,并基于现阶段研究的不足,对未来发展方向提出设想。Trust-vectoring nozzle can visibly enhance the maneuverability of aircraft. The applications of mechan-ical vectoring-nozzle are limited due to the complicated structure and poor reliability, while the pneumatic vecto-ring-nozzle has a better performance. Series of pneumatic vectoring-nozzle are developed in recent years. The development of pneumatic-vector-control technology is introduced briefly. The research progress on the aerody-namic performance and configuration optimization of dual throat nozzle is reviewed in detail. Problems in exist-ing research are summarized and the future developments of dual throat nozzle are prospected.

关 键 词：双喉道喷管 推力矢量 气动特性 构型优化 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]