摘要
针对直升机/舰船动态适配中风限图试验风险高、耗时长的特点,文章对直升机的舰面悬停风限图计算展开研究。首先将关于直升机操纵量、姿态角和功率的判据引入直升机舰面起降飞行动力学模型,建立风限图计算模型;然后进行舰面悬停平衡仿真,获得了某型无人直升机的舰面悬停风限图。计算结果表明,风限图计算模型能够给出不同来流风向、风速的舰面流场环境限制的风限图,对算例直升机的风限图试验具有较大的指导意义。
In view of the high risk and time-consuming characteristics of helicopter/ship dynamic combining Wind Over Deck(WOD)envelope test,this paper studies the calculation of helicopter shipboard hover WOD envelope.Firstly,the WOD envelope calculation model is established by introducing the criteria of helicopter control,attitude angle and power are introduced into the flight dynamics model of helicopter shipboard operations.Then,the shipboard hovering balance simulation is carried out,and the WOD envelope of an unmanned helicopter is obtained.The calculation results show that the WOD envelope calculation model established can give the WOD envelope of the shipboard flow environmental limit with different inflow wind direction and wind speed,which has great guiding significance for the WOD envelope test of helicopter.
作者
唐宏清
肖升兴
TANG Hongqing;XIAO Shengxing
出处
《科技创新与应用》
2020年第36期19-21,共3页
Technology Innovation and Application
关键词
直升机
飞行动力学模型
风限图
平衡仿真
helicopter
flight dynamics model
WOD envelope
balance simulation
