斜风来流下纵摇运动对机-舰耦合流场的影响

李通; 刘戈; 宗昆; 赵宁; 王逸斌

doi:10.7638/kqdlxxb-2022.0174

斜风来流下纵摇运动对机-舰耦合流场的影响

doi: 10.7638/kqdlxxb-2022.0174

李通^1,,
刘戈¹,
宗昆^{1, 2, ,},
赵宁³,
王逸斌³

1.
中国船舶集团有限公司系统工程研究院，北京　100094
2.
哈尔滨工程大学船舶工程学院，哈尔滨　150001
3.
南京航空航天大学非定常空气动力学与流动控制工业和信息化部重点实验室，南京　210016

详细信息

作者简介:
李通（1995-），男，陕西人，工程师，研究方向：舰面流场数值计算. E-mail：lee_tong@foxmail.com

通讯作者:
宗昆^*（1987-），男，高级工程师，研究方向：航空保障技术. E-mail：839159704@qq.com

中图分类号: V211.3
计量
- 文章访问数: 45
- HTML全文浏览量: 20
- PDF下载量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2022-10-21
- 录用日期: 2022-12-04
- 修回日期: 2022-11-28
- 网络出版日期: 2023-01-31
- 刊出日期: 2023-03-25

Influence of pitching on ship-helicopter coupled flowfield subject to oblique winds

LI Tong^1
,,
LIU Ge¹,
ZONG Kun^{1, 2
, ,},
ZHAO Ning³,
WANG Yibin³

1.
Systems Engineering Research Institute, CSSC, Beijing　100094, China
2.
College of Shipbuilding Engineering, Harbin Engineering University, Harbin　150001, China
3.
Key Laboratory of Unsteady Aerodynamics and Flow Control of Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics , Nanjing　210016, China

摘要

摘要: 机-舰耦合流场是一个复杂紊乱的非定常流场，舰船的六自由度摇摆运动会进一步恶化飞行甲板上方的流场环境。为了探究舰船的摇摆运动对飞行甲板上方机-舰耦合流场的影响，基于简化护卫舰SFS2和旋翼的耦合模型，对两种斜风状态下、纵摇运动中的机-舰耦合流场进行了数值模拟，分析了纵摇运动对机-舰耦合流场结构和旋翼拉力的影响，对比了两种斜风状态下的流场差异。研究结果表明：随着舰船的纵摇运动，机库后方形成的不稳定混合涡结构和垂向气流会对旋翼气动力造成明显的影响，旋翼拉力出现了近似周期性的变化，与纵摇运动的周期一致，但各观测点处的速度分量均未出现周期性的变化；旋翼拉力在甲板上浮至水平位置附近时最大，在甲板下沉至水平位置附近时最小，对于左舷和右舷来流，拉力分别降低了约13%和6%，因此飞行员要认识到纵摇运动带来的拉力损失，确保直升机具有足够的操纵量，以便能及时调整总距来保证直升机在该状况下的起降安全性。
- 舰面流场 /
- 机-舰耦合流场 /
- 非定常 /
- 纵摇 /
- 计算流体力学
Abstract: Ship-helicopter coupled unsteady flowfield are complicated and disordered, and the six-degree-of-freedom motion of the ship will further worsen the flowfield environment above the flight deck. This paper conducted numerical simulations of the pitching ship-helicopter coupled flowfield under two kinds of oblique wind conditions by computational fluid dynamics (CFD) method using the model of simplified frigate SFS2 and rotor. The influence of the pitching motion on the coupled flowfield structure and rotor’s thrust is analyzed, and the differences in the flowfield under the two conditions are compared. Results show that, with the pitching motion of the ship, the unstable mixed vortical structures and vertical airflow formed behind the hangar will affect the rotor's aerodynamic force. The rotor’s thrust changes approximately periodically, consistent with the pitching motion period, but the velocity components at each observation point do not. The rotor’s thrust is maximum when the deck goes up to the horizontal position and minimum when the deck sinks to the horizontal position. For the port and starboard wind, the thrust decreases by about 13% and 6%, respectively. Therefore, pilots should be aware of the thrust loss caused by the pitching motion, ensure that the helicopter has enough operating margin, and timely adjust the collective pitch to enhance the helicopter’s take-off and landing safety in this situation.
- ship airwake /
- ship-helicopter coupled flowfield /
- unsteady /
- pitching /
- computational fluid dynamics

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图 1 SFS及SFS2模型示意图

Figure 1. Schematic of SFS and SFS2

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图 2 交界面示意图

Figure 2. Schematic of interface

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图 3 计算结果验证

Figure 3. Comparisons of calculated and experimental results

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图 4 机舰耦合模型示意图

Figure 4. Schematic of rotor-ship coupled model

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图 5 流场域示意图

Figure 5. Schematic of flow field

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图 6 网格示意图

Figure 6. Schematic of grid

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图 7 不同网格下的旋翼拉力变化

Figure 7. Variation of rotor thrust for different grids

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图 8 R30°的涡结构分布图

Figure 8. Distribution of vortex structure in R30°

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图 9 R30°的涡量云图

Figure 9. Distribution of vorticity in R30°

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图 10 R30°的垂向速度云图

Figure 10. Distribution of vertical velocity in R30°

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图 11 R30°状态下的旋翼拉力变化

Figure 11. Variations of rotor thrust in R30° state

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图 12 R30°状态下观测点的速度分量变化

Figure 12. Variations of velocity components in R30° state

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图 13 G30°的涡结构分布图

Figure 13. Distribution of vortical structures in G30°

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图 14 G30°的涡量云图

Figure 14. Distribution of vorticity in G30°

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图 15 G30°的垂向速度云图

Figure 15. Distribution of vertical velocity in G30°

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图 16 G30°状态下的旋翼拉力变化

Figure 16. Variations of rotor thrust in G30° state

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图 17 G30°状态下观测点的速度分量变化

Figure 17. Variations of velocity components in G30° state

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图 18 两种状态下的旋翼拉力对比

Figure 18. Comparisons of rotor thrust between two states

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图 19 两种状态下的速度分量对比

Figure 19. Comparisons of velocity components between two states

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