南京航空航天大学学报2024，Vol.56Issue(2)：227-233,7.DOI:10.16356/j.1005-2615.2024.02.004
基于CFD方法的舰载直升机着舰风限图计算
Shipborne Helicopter Operational Limits Calculation Based on CFD Method
左清宇 1徐国华 1史勇杰1
作者信息
- 1. 南京航空航天大学直升机动力学全国重点实验室,南京 210016
- 折叠
摘要
Abstract
A helicopter landing flow field calculation method based on Navier Stokes equations is established,which can be applied to the calculation of aerodynamic forces on the rotor,fuselage and tail rotor in the landing area.The method uses a cut-body grid for meshing,an implicit coupling solver and a dual-time scheme to simulate the flow field during the landing process.To improve the computational efficiency,the main rotor and tail rotor are modeled as momentum sources in the flow field.The method also employs a polynomial fitting technique to correct the results of the nonlinear flight dynamics model of the helicopter and achieve trim calculations in complex flow fields.The method is applied to the UH-60A helicopter and the SFS2 ship as case studies.First,a single-helicopter trim analysis coupled CFD method is performed to verify its validity.Then,the helicopter safe landing criteria are introduced and used to calculate the theoretical ship helicopter operational limitation for this helicopter/ship combination.关键词
直升机空气动力学/舰载直升机/飞行动力学/配平分析/理论风限图Key words
helicopter aerodynamics/shipborne helicopter/flight dynamics/trimming analysis/ship helicopter operational limitation分类
航空航天引用本文复制引用
左清宇,徐国华,史勇杰..基于CFD方法的舰载直升机着舰风限图计算[J].南京航空航天大学学报,2024,56(2):227-233,7.
