舰艉流场主动控制对直升机配平操纵的影响

叶毅; 陈仁良

doi:10.13224/j.cnki.jasp.20220646

舰艉流场主动控制对直升机配平操纵的影响

doi: 10.13224/j.cnki.jasp.20220646

叶毅,
陈仁良^*, ,

南京航空航天大学航空学院直升机动力学全国重点实验室，南京 210016

基金项目: 国家自然科学基金（11672128）；江苏高校优秀学科建设工程资助项目

详细信息

作者简介:
叶毅（1992-），男，博士生，研究方向为直升机飞行力学与控制

通讯作者:
陈仁良（1963-），男，教授、博士生导师，博士，研究方向为直升机多学科优化设计、直升机飞行力学与控制、直升机空气动力学。E-mail：crlae@nuaa.edu.cn

中图分类号: V212.4
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- 被引次数: 0
出版历程
- 收稿日期: 2022-08-31
- 网络出版日期: 2024-03-04

Effect of ship airwake active control on helicopter trimmed controls

YE Yi,
CHEN Renliang^{*
, ,}

National Key Laboratory of Helicopter Aeromechanics，College of Aerospace Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为研究舰艉流场对直升机配平操纵的影响，采用了数值模拟和直升机飞行动力学模型相结合的方法，通过computational fluid dynamics（CFD）数值模拟得到舰艉流场，并探究加入流场主动控制下的舰艉流场特征，同时考虑舰艉流场对直升机的影响，建立耦合的直升机舰面起降飞行动力学模型。计算得到直升机在有无艉流下相对悬停配平结果，并进一步对比分析有无流场主动控制对直升机配平操纵的影响。结果表明：舰艉流场对直升机起降影响显著，且相比较于无控制时舰艉流场对直升机操纵的干扰，增设吹气装置可有效抑制舰艉流场下洗，减小所需总距操纵杆量7.8%，脚蹬操纵量7.5%，改善其他相应操纵，减轻驾驶员操纵负荷。
- 舰艉流场 /
- 流场主动控制 /
- 耦合飞行动力学 /
- 直升机配平操纵 /
- 安全起降
Abstract:
In order to investigate the effect of ship airwake on helicopter trimmed controls, a method of combining numerical simulation and helicopter flight dynamics model was adopted. The ship airwake was obtained by computational fluid dynamics (CFD) numerical simulation method, and the characteristics of ship airwake under active control were explored; at the same time, considering the effect of ship airwake on helicopter, the flight dynamics model coupled with the ship airwake was established. The results of relative hovering trim with/without airwake were calculated, and the effect of active control on helicopter trimmed controls was further compared and analyzed. The results showed that the ship airwake had a significant impact on the helicopter take-off and landing, compared with the interference of the ship airwake on the helicopter controls when there was no control, the addition of the blowing device can effectively suppress the downwash of the ship airwake, reduce the required collective pitch control by 7.8% and pedal control by 7.5%, improve other corresponding controls and alleviate the pilot control load.
- ship airwake /
- active control /
- coupled flight dynamics /
- helicopter trimmed controls /
- safe take-off and landing

HTML

图 1 验证舰船网格细节示意图

Figure 1. Schematic of verified ship mesh details

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图 2 数值模拟结果与文献实验对比

Figure 2. Comparison of numerical simulation results with literature experiments

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图 3 某型舰船网格细节示意图

Figure 3. Schematic of a certain type of ship mesh details

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图 4 坐标系及分析区域示意图

Figure 4. Schematic of coordinate system and analysis areas

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图 5 原始舰船舰艉XZ平面流线（横向0 m）

Figure 5. XZ plane streamline of stern of original ship （horizontal 0 m）

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图 6 原始舰船舰艉XY平面流线（高度2.5 m）

Figure 6. XY plane streamline of stern of original ship （height 2.5 m）

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图 7 有无舰船艉流操纵量对比

Figure 7. Comparison of control variables with and without ship airwake

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图 8 吹气装置示意图

Figure 8. Schematic of blowing device

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图 9 主动控制XZ平面流线（横向0 m）

Figure 9. XZ plane streamline of active control （horizontal 0 m）

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图 10 主动控制XY平面流线（高度2.5 m）

Figure 10. XY plane streamline of active control （height 2.5 m）

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图 11 有无主动控制操纵量对比

Figure 11. Comparison of control variables with and without active control

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