舰面流场下的直升机平衡特性分析  

Analysis of shipboard helicopter trim characteristics in airwake

作　　者：徐广[1] 胡国才[1] 陶杨[1] 王允良[1] 

机构地区：[1]海军航空工程学院飞行器工程系,山东烟台264001

出　　处：《飞行力学》2015年第2期116-119,124,共5页Flight Dynamics

基　　金：航空科学基金资助(20145784010)

摘　　要：主要分析了舰载直升机在母舰甲板上方悬停时的平衡特性。采用CFD方法计算了母舰甲板上方的气流场,建立了适用于舰载环境的直升机飞行动力学模型,计算了UH-60A直升机在流场悬停位置处的配平值。在此基础上,计算了旋翼入流、载荷、功率以及机体姿态状态量的响应。仿真结果表明,舰面流场的非线性、不均匀等特点对计算值影响较大。通过与无离散模型计算结果的对比,表明了流场对直升机旋翼的垂向载荷影响较大,对机体姿态角速率的影响更为显著,破坏了直升机的平衡,对直升机在舰面流场环境下的飞行控制系统提出了更高的要求。In this paper,we focus on the trim characteristics of shipboard helicopter in hover on the deck. The airflow field above the deck is calculated by CFD method. The flight dynamic model of shipboard environment is established. The trim values of UH-60 A helicopter trimming in hover are calculated. On this basis,the main rotor inflow,load,power and the response of flight attitude values are calculated. The conclusion shows that the characteristics of nonlinear and inhomogeneous airwake have great influence on the results. In addition,the contrast with the result of non-division model indicates that the airflow field has more significant influence on helicopter vertical loads,and a great change on attitude angle rate,destroying the helicopter trim condition,which places a great demand for the flight stabilization system in shipboard environment.

关 键 词：舰面流场 舰载直升机 平衡特性 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]