直升机在复杂舰面流场中的悬停研究  

Research on Helicopter Hover on Flight Deck in Complicated Airflow Field

作　　者：徐广[1] 胡国才[1] 王允良[1] 柳泉[1] 

机构地区：[1]海军航空工程学院飞行器工程系,烟台264001

出　　处：《南京航空航天大学学报》2015年第2期205-211,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：航空科学基金(20145784010)资助项目

摘　　要：针对舰面流场非线性、非均匀的特性,把旋翼桨盘离散成空间有限单元,将当地流场风速叠加到叶素剖面相对气流中,改进了叶素气动力计算模型,提高了旋翼载荷的计算精度;采用CFD方法计算了某型母舰甲板上方的气流场,其下冲气流是影响直升机安全的主要因素;计算了UH-60A直升机在该舰甲板4个直升机起降位上方流场中的悬停配平,通过与陆基环境计算结果的对比,分析了舰面流场环境对直升机舰面悬停性能的影响;同时,计算了直升机在舰面流场中的响应,通过对MIL流场模型响应的对比验证了本文计算模型。.As for the characteristics of nonlinear and inhomogeneous airflow field, rotor disk is divided in- to elements by the method of spatial discretization. Local speed of flow field is superimposed to the ele- ment relative flow, the calculation model of element aerodynamic force is improved, and the calculation precision of rotor loads is increased. The airflow field on the deck is calculated by CFD method, and the downwash airflow is the key influence factor on helicopter safety. Taking UH-60A helicopter for exam- ple, the trim values of helicopter in hover are calculated in four landing zones on flight deck. By contrast with the results in ground-based condition, the influence and the causation of airflow field on hover char- acteristics are analyzed. In addition, the helicopter flight response in airflow field on the deck is also cal- culated and compared with the resDonse in MIL models, which Droves the proposed model.

关 键 词：直升机 舰面流场 舰面悬停 飞行动力学 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]