直升机复合材料尾传动轴弹击损伤及剩余强度试验研究

叶飞; 蔡逸飞; 尹凌; 刘之扬; 龙俊米; 王希; 聂慧阳; 王旦

doi:10.13224/j.cnki.jasp.20250006

直升机复合材料尾传动轴弹击损伤及剩余强度试验研究

doi: 10.13224/j.cnki.jasp.20250006

叶飞¹,
蔡逸飞²,
尹凌¹,
刘之扬³,
龙俊米³,
王希³,
聂慧阳³,
王旦^2,*, ,

1.
陆军装备部某部，湖南株洲 412002
2.
南京航空航天大学机电学院，南京 210016
3.
中国航发湖南动力机械研究所直升机动力学全国重点实验室，湖南株洲 412002

基金项目: 国家自然科学基金（52005253）；南京航空航天大学基本科研业务费（NS2024028）

详细信息

作者简介:
叶飞（1983-），男，硕士，主要研究方向为航空宇航推进理论与工程

通讯作者:
王旦（1990-），男，副教授，博士，主要研究方向为直升机先进传动技术。E-mail：wangdan_053@nuaa.edu.cn

中图分类号: V228.5
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- 文章访问数: 497
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- 被引次数: 0
出版历程
- 收稿日期: 2025-01-03
- 网络出版日期: 2026-04-05

Experimental study on impact damage and residual strength of composite tail drive shaft for helicopter

1.
Certain Unit of the Army Equipment Department，Zhuzhou Hunan 412002，China
2.
College of Mechanical and Electrical Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
3.
National Key Laboratory of Helicopter Aeromechanics，Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
为研究不同制备工艺和弹击工况对直升机尾传动轴弹击损伤及剩余强度的影响，分别制备了编织型和缠绕型复合材料尾传动轴，基于轻气炮装置和扭转试验机开展了典型工况下的弹击试验和扭转试验。研究结果表明：相比于子弹入射角度，子弹偏移量对尾传动轴损伤程度的影响更为显著；从制备工艺的角度来看，相比于缠绕型尾传动轴，编织型复合材料尾传动轴表现出更优异的抗弹击损伤性能；从失效模式的角度来看，无损和贯穿式弹击工况下复合材料尾传动轴在扭转试验中的失效模式表现为瞬间断裂，而切边式弹击工况下复合材料尾传动轴在扭转试验中的失效模式表现为渐进断裂。
- 直升机尾传动轴 /
- 复合材料 /
- 弹击试验 /
- 扭转试验 /
- 抗弹击设计
Abstract:
To investigate the effects of different manufacturing processes and impact conditions on the impact damage and residual strength of helicopter tail drive shafts, braided and filament-wound composite tail drive shafts were fabricated, and impact and torsion tests under typical conditions were conducted using a light gas gun device and a torsion testing machine. The results showed that, compared with the bullet's incident angle, the bullet's offset had a more significant effect on the damage degree of the tail drive shaft. From the perspective of manufacturing processes, the braided composite tail drive shaft exhibited superior impact damage resistance compared with the filament-wound tail drive shaft. From the perspective of failure modes, under non-damaging and through-penetration impact conditions, the failure mode of the composite tail drive shaft in torsion tests was characterized by instantaneous fracture, whereas under edge-cutting impact conditions, the failure mode in torsion tests was characterized by progressive fracture.
- helicopter tail drive shaft /
- composite material /
- impact test /
- torsion test /
- impact-resistant design

HTML

图 1 复合材料尾传动轴试验件及细观结构

Figure 1. Composite tail drive shaft test specimens and mesoscale structures

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图 2 尾传动轴弹击试验系统图

Figure 2. Impact test system diagram of tail drive shaft

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图 3 弹击工况参数示意图

Figure 3. Schematic diagram of impacting condition parameters

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图 4 尾传动轴损伤模式示意图

Figure 4. Schematic diagram of tail drive shaft damage modes

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图 5 典型工况下尾传动轴弹击前后子弹的速度衰减

Figure 5. Bullet velocity attenuation before and after tail drive shaft impact under typical conditions

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图 6 4种典型工况下编织型复合材料尾传动轴弹击损伤历程

Figure 6. Impact damage process of braided composite tail drive shaft under four typical conditions

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图 7 4种典型工况下缠绕型复合材料尾传动轴弹击损伤历程

Figure 7. Impact damage process of filament-wound composite tail drive shaft under four typical conditions

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图 8 4种典型工况下编织型复合材料尾传动轴弹击损伤形貌

Figure 8. Impact damage morphology of braided composite tail drive shaft under four typical conditions

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图 9 4种典型工况下缠绕型复合材料尾传动轴弹击损伤形貌

Figure 9. Impact damage morphology of filament-wound composite tail drive shaft under four typical conditions

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图 10 尾传动轴扭转试验装置

Figure 10. Tail drive shaft torsion test device

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图 11 典型工况下$ [{0}{\text{°}}/\pm 6{0}{\text{°}}{]}_{5} $编织型复合材料受损尾传动轴的扭转破坏曲线

Figure 11. Torsional failure curve of damaged tail drive shaft made of $ [{0}{\text{°}}/\pm 6{0}{\text{°}}{]}_{5} $ braided composite under typical conditions

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图 12 典型工况下$ [\pm 1{4}{\text{°}}/\pm 4{5}{\text{°}}/\pm 4{5}{\text{°}}/\pm 1{4}{\text{°}}{]}_{\mathrm{s}} $缠绕型复合材料受损尾传动轴的扭转破坏曲线

Figure 12. Torsional failure curve of damaged tail drive shaft made of $ [\pm 1{4}{\text{°}}/\pm 4{5}{\text{°}}/\pm 4{5}{\text{°}}/\pm 1{4}{\text{°}}{]}_{\mathrm{s}} $ filament-wound composite under typical conditions

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图 13 无损工况下复合材料尾传动轴的扭转破坏形貌

Figure 13. Torsional failure morphology of undamaged composite tail drive shafts

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图 14 0°贯穿工况下复合材料尾传动轴的扭转破坏形貌

Figure 14. Torsional failure morphology of composite tail drive shafts under 0° through-penetration condition

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图 15 45°切边工况下复合材料尾传动轴的扭转破坏形貌

Figure 15. Torsional failure morphology of composite tail drive shafts under 45° edge-cutting condition

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图 16 $ [\pm 1{4}{\text{°}}/\pm 4{5}{\text{°}}/\pm 4{5}{\text{°}}/\pm 1{4}{\text{°}}{]}_{\mathrm{s}} $缠绕型复合材料尾传动轴和$ [{0}{\text{°}}/\pm 6{0}{\text{°}}{]}_{5} $编织型复合材料尾传动轴在不同弹击工况下的极限承载扭矩

Figure 16. Ultimate torsional load capacity of $ [\pm 1{4}{\text{°}}/\pm 4{5}{\text{°}}/\pm 4{5}{\text{°}}/\pm 1{4}{\text{°}}{]}_{\mathrm{s}} $ filament-wound composite tail drive shaft and $ [{0}{\text{°}}/\pm 6{0}{\text{°}}{]}_{5} $ braided composite tail drive shaft under different impact conditions

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