折叠机翼展开过程气动特性实验研究  

Experimental study of aerodynamic characteristics in floding wings deployment process

作　　者：吕胜利[1] 刘平[2] 杨广珺[1] 童小燕[1] 

机构地区：[1]西北工业大学无人机特种技术国家重点实验室,陕西西安710065 [2]西北工业大学航空学院,陕西西安710072

出　　处：《飞行力学》2013年第1期80-83,共4页Flight Dynamics

摘　　要：针对某型无人机大展弦比折叠机翼展开过程,对其缩比模型在不同迎角、不同机翼掠角状态下的气动特性进行了风洞实验。实验结果表明,布局的气动外形满足巡航设计要求,纵向与横航向稳定性较好,多面组合式机身表面可为全机升力带来有利影响,研究结果可在无人机、巡飞导弹等研究领域得到应用。According to the deployment process of high-aspect-ratio UAV floding wings, aerodynamic characteristics is studied on scaled model at different attack angle and different grazing angle for wind tun- nel test. Experimental results show that layout of aerodynamic configuration can meet design requirements of cruise, and it has a good stability at vertical and transverse course. Multi-surface combined Fuselage can bring favorable effect on full-aircraft. Characteristic analysis points out the direction of aerodynamic shape optimization. Results can be applied in the research areas of UAV and loiter attack missile.

关 键 词：展弦比 气动特性 风洞实验 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V279