中国民航大学学报 ›› 2024, Vol. 42 ›› Issue (6): 91-96.

• 通用航空与无人机 • 上一篇    

某型无人机阻尼减振器分析与改进设计

刘艳红, 李浩峰
  

  1. 中国民航大学航空工程学院,天津 300300
  • 收稿日期:2022-11-01 修回日期:2023-01-05 出版日期:2025-04-08 发布日期:2025-04-08
  • 作者简介:刘艳红(1970— ),女,河南驻马店人,博士,教授,研究方向为复合材料结构力学
  • 基金资助:
    国家自然科学基金项目(11502286)

Damping vibration absorber analysis and improved design of a certain UAV

LIU Yanhong, LI Haofeng
  

  1. College of Aeronautical Engineering, CAUC, Tianjin 300300, China
  • Received:2022-11-01 Revised:2023-01-05 Online:2025-04-08 Published:2025-04-08

摘要:

针对某型油电混用无人机巡航阶段对机身振动的控制要求,本文基于被动减振原理设计了发动机与机身连
接处的 4 点和 6 点式布局的阻尼减振器,并将两种布局形式的减振器装机后在地面模拟无人机飞行状态,
得到实验测试结果与原始减振器进行对比。 结果表明,两种布局形式的减振器均可以使机身振动得到有效
控制,其中,6 点式布局的阻尼减振器的减振效果更好,使得机身振动的各项指标均满足要求,同时通过减
少减振器的重量对该无人机进行了减重。

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Abstract:

Considering the control requirements of fuselage vibration for a certain type of oil-electric hybrid unmanned aerial
vehicle (UAV) during cruise phase, the damping vibration absorbers with 4-point and 6-point layout at the connection between the engine and the fuselage are designed in this paper based on the passive vibration reduction principle. After installing the two types of vibration absorbers, the flight state of the UAV are simulated on the ground, The
experimental test result is compared with original vibration absorber. The results indicate that both types of vibration absorbers can effectively control the fuselage vibration, and the damping vibration absorbers with the 6-point
layout having a better effect of vibration reduction, which ensuring each indicator of the fuselage vibration meet the
requirements. At the same time, the weight of the UAV has been reduced by reducing the weight of the vibration
absorbers.

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