摘要
折叠式直升机由于折叠后体积小,便于地面或舰艇上停放、运输,展开后又具备飞行器的飞行功能,其应用领域不断扩大。折叠式直升机一项最关键的技术就是对机翼折叠展开作动器机构的设计。本文针对某单位提出的某型折叠翼作动器机构技术要求,设计了一种新的折叠翼作动器机构,后经有限元软件仿真,并对制造出来的实物进行了试验验证,其性能均满足技术协议要求。
Folding helicopters due to the small size after folding,easy to park on the ground or ships,transport,expand and have the aircraft after the flight function,its application areas continue to expand.One of the most critical technologies for folding helicopters is the design of the wing folding actuators.In this paper,a new folding wing actuator mechanism was designed for the technical requirements of a certain type of folding wing actuator mechanism proposed by a unit.After the simulation of the finite element software,the test results were verified by the finite element software,meet the technical agreement requirements.
作者
彭若晨
丁帅
窦满峰
PENG Ruochen;DING Shuai;DOU Manfeng(Northwestern Polytechnical University,Xi'an 710129,China)
出处
《微电机》
北大核心
2018年第3期6-10,23,共6页
Micromotors
关键词
直升机
折叠机翼
折叠机构
仿真
试验
Helicopter
Folding wing
Folding mechanism
Simulation
Test
作者简介
彭若晨(1994),男,硕士研究生,研究方向为稀土永磁电机设计。;丁帅(1994),男,硕士研究生,研究方向为现代电机控制技术。;窦满峰(1967),男,教授,博士生导师,研究方向为稀土电机及智能控制、航空航天特种电机及节能电机控制。
