| 杨仕福,周立胜,杨荣,李俊龙.某大型涡桨飞机副翼振动与控制研究[J].装备环境工程,2024,21(9):19-25. YANG Shifu,ZHOU Lisheng,YANG Rong,LI Junlong.Aileron Vibration and Control of a Large Turboprop Aircraft[J].Equipment Environmental Engineering,2024,21(9):19-25. |
| 某大型涡桨飞机副翼振动与控制研究 |
| Aileron Vibration and Control of a Large Turboprop Aircraft |
| 投稿时间：2024-08-09 修订日期：2024-08-21 |
| DOI：10.7643/issn.1672-9242.2024.09.003 |
| 中文关键词: 受迫振动 操纵系统 频率响应 旋转频率 飞行试验 动刚度中图分类号:V225 文献标志码:A 文章编号:1672-9242(2024)09-0019-07 |
| 英文关键词:forced vibration control system frequency response rotation frequency flight test dynamic stiffness |
| 基金项目:工信部民机预研课题(HN-2024-KJ-06004) |
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| Author | Institution |
| YANG Shifu | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519040, China |
| ZHOU Lisheng | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519040, China |
| YANG Rong | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519040, China |
| LI Junlong | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519040, China |
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| 中文摘要: |
| 根据适航规章要求，研究了飞机操纵面振动设计要求和方法，论述了飞机操纵面作动器动刚度和自由间隙极限环振荡计算方法。针对某大型涡桨飞机在试飞中发现的副翼振动问题，论述了副翼异常振动产生的原因，建立了结构动力学有限元模型，开展副翼操纵刚度、阻尼变参的频率响应分析，研究副翼的振动特性。提出了副翼助力器活塞打孔增加阻尼的临时改进方法，及根据操纵面振动设计、自由间隙控制要求的副翼结构和系统优化方法。副翼改进设计后，试飞数据分析表明，副翼的振动响应幅值降幅明显，振动收敛性较好，保障了型号试飞的继续开展。 |
| 英文摘要: |
| According to airworthiness regulations, the design requirements and methods of aircraft control surface vibration werestudied. The calculation methods of actuator dynamic stiffness and free clearance limit cycle oscillation of aircraft control surface were discussed. Aiming at the aileron vibration problem found in flight test of a large turboprop aircraft, the causes of the abnormal aileron vibration were expounded, and the finite element model of structural dynamics was established to carry out the frequency response analysis of aileron control stiffness and damping with variable parameters and study the vibration characteristics of aileron. Then, a temporary method to improve the damping of aileron booster piston by punching holes and a method to optimize aileron structure and system according to the requirements of control surface vibration design and free clearance control were proposed. After the improved design of aileron, the analysis of test flight data showed that the vibration response amplitude of aileron decreased obviously and the vibration convergence was good, guaranteeing the continued development of the flight test. |
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