基于CFD的舰载直升机起降理论风限图研究
Study of Theoretical Flight Envelop for Ship-borne Helicopter Takeoff and Landing Based on CFD
投稿时间:2020-06-01  修订日期:2020-06-01
DOI:10.13788/j.cnki.cbgc.2020.05.02
中文关键词:  舰载直升机  动量源  耦合流场  理论风限图
英文关键词:ship-borne helicopter  momentum source  coupled flowfield  theoretical flight envelop
基金项目:
作者单位E-mail
黄 斌 中国船舶及海洋工程设计研究院 18616780319@163.com 
郝 桐 中国船舶及海洋工程设计研究院  
赵启兵 中国船舶及海洋工程设计研究院  
何 巍 中国船舶及海洋工程设计研究院  
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中文摘要:
      基于CFD技术建立了一种舰载直升机配平分析方法,以动量源的形式计入直升机旋翼作用,用于分析舰船/直升机之间的耦合干扰问题,并可实现舰机耦合干扰流场的快速计算,突破了原先飞行力学模型中气动参数单向耦合方式的局限性。在该方法中,控制方程选取N-S方程,湍流模型为k-e模型,求解方式采用隐式耦合方式,网格上运用自适应切割体网格进行划分,并引入舰载直升机安全着舰判据,发展了一个可用于计算舰载直升机着舰理论风限图的模型。应用建立的方法,以黑鹰直升机作为算例,与试验值进行了对比,验证了方法的有效性。在此基础上应用该模型计算得出了特定舰机组合下的理论风限图。
英文摘要:
      A trim analysis method for ship-borne helicopter based on CFD technology is established. Incorporating the helicopter rotor action in the form of momentum source, it is used to analyze the coupling interference between the ship and the helicopter, and can realize the fast calculation of the coupling interference flow field of the ship, breaking through the one-way coupling of aerodynamic parameters in the original flight mechanics model Limitations of the method. In the method, N-S equation is selected as the governing equation, the k-e model is used as the turbulence model and the implicit method is employed as solver method. An adaptive trimmed mesh is used to generate the grid of computational regions. Through introducing helicopter landing security criterion, a model that can be used to calculate the ship-borne helicopter flight envelop is developed. Applying the established method, the Black Hawk helicopter is taken as the calculation example to compare with experimental data. The effectiveness of the method is verified. Then, by the model a theoretical flight envelop for specific combination of ship and helicopter is calculated.
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