舰载直升机主动甲板着舰气动载荷特性  

Investigation on aerodynamics of a helicopter approaching an active control deck

作　　者：谭剑锋[1] 邢肖兵 崔钊 武杰[3] 张卫国[3] TAN Jianfeng;XING Xiaobing;CUI Zhao;WU Jie;ZHANG Weiguo(School of Mechanical and Power Engineering,Nanjing Tech University,Nanjing 211816,China;Aircraft Institute of Technical Center,Chinese Flight Test Establishment,Xi’an 710089,China;Rotor Aerodynamics Key Laboratory,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]南京工业大学机械与动力工程学院,南京211816 [2]中国飞行试验研究院技术中心飞机所,西安710089 [3]中国空气动力研究与发展中心旋翼空气动力学重点实验室,绵阳621000

出　　处：《北京航空航天大学学报》2024年第7期2206-2217,共12页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(12172165);江苏省自然科学基金(BK20211259);江苏省青蓝工程“优秀青年骨干教师”项目。

摘　　要：被动与主动流动控制可减小舰艇艉流强度,但直升机着舰甲板处仍存在明显回流现象,由此导致直升机气动载荷变化显著。提出了自动升降的舰艇主动甲板,建立基于格子玻尔兹曼方法 (LBM)的舰艇主动甲板流场分析方法,并结合单向耦合模型,嵌入旋翼黏性涡粒子法,研究直升机主动甲板着舰气动载荷特性。通过与SFS2舰艇流场试验、分离涡模拟(DES)方法、大涡模拟(LES)方法比较,验证了所建方法的准确性。随后研究主动甲板对舰艇流场和直升机着舰气动载荷的影响特性。结果表明:相比于标准SFS2舰艇,主动甲板有效抑制了直升机着舰甲板处回流,以及直升机旋翼拉力损失、滚转和俯仰力矩,最大降幅分别为21.6%、55.1%、74.6%。Passive and active flow controls were used to reduce the turbulence intensity of ship airwake,but there was a recirculation zone on the deck resulting in intensively unsteady airloads of a helicopter.Thus,a novel active control deck(ACD) which can be automatically lifted up and descended is firstly proposed to weaken the recirculation.Helicopter airloads are examined by combining a viscous vortex particle approach with the lattice Boltzmann approach(LBM) via a one-way coupling model.This establishes a flow field analysis method of the ship with ACD.The accuracy of the method is validated by comparing the present prediction with the SFS2 experiment,detached eddy simulation(DES),and large eddy simulation(LES) results.The influences of the ACD on the ship flow field and airloads of a helicopter approaching the ship are analyzed.It is demonstrated that the ACD clearly suppresses the recirculation bubble when compared to the baseline SFS2.Additionally,the reduction of the rotor thrust,rolling,and pitching moments is weakened,with the largest reductions being 21.6%,55.1%,74.6%.

关 键 词：主动甲板 直升机旋翼 舰艇艉流 格子玻尔兹曼方法 黏性涡粒子 

分 类 号：V221.52[航空宇航科学与技术—飞行器设计] TB553[理学—物理]