四连杆铰链襟翼机构方案设计分析与优化  

Analysis and optimization of four-bar linkage hinge flap mechanism

作　　者：郭仕贤 柴啸 Guo Shixian;Chai Xiao(Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China Co.,Ltd.,Shanghai,201210,China)

机构地区：[1]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2024年第10期36-40,共5页Machine Design and Manufacturing Engineering

摘　　要：最新的大型宽体客机均采用了新型铰链襟翼形式,国内缺乏对铰链襟翼具体结构连接设计和驱动载荷分析方面的研究。为了使气动方案更好地落实到具体机构方案中,开展了四连杆铰链襟翼机构方案设计,包含运动副设计、机构参数设计,进行了机构传载分析。建立了动力学仿真分析模型,综合权衡驱动器位置、襟翼驱动点位置、驱动摇臂的长度和连杆的长度等参数对驱动载荷进行优化,优化后驱动载荷降低了约14%。襟翼机构设计方案确保了气动方案与结构方案的匹配性和可实现性,可指导国内自主开展铰链襟翼机构设计。The latest large wide-body passenger aircraft have adopted new type of hinge flaps,and there is still a lack of research on the specific structural connection design and driving load analysis of hinge flaps in China.In order to better implement the aerodynamic results into the specific mechanism structure design,a four-bar linkage hinge flap mechanism design is carried out,including kinematic pair design,mechanism parameter design,and mechanism load transmission analysis.A dynamic simulation analysis model is established to optimize the driving load by considering parameters such as the position of the actuator,the position of the flap driving point,the length of the driving rocker arm,and the length of the connecting rod.After optimization,the driving load is reduced by about 14%.The design of the flap mechanism ensures the matching and feasibility between the aerodynamic and the structural scheme,which can guide the independent development of hinge flap mechanism design in China.

关 键 词：增升装置 四连杆机构 襟翼 机构设计 驱动载荷分析 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]