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大型客机缝翼静力试验姿态调节装置设计 预览

Design of the angle adjustment device for slat static test on large airliner
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摘要 为满足大型客机前缘缝翼结构全尺寸静力试验验证需求,设计了一套缝翼试验件姿态调节装置。该姿态调节装置由齿条模拟件、齿轮模拟件、轴承、螺栓等零件组成,结构设计合理,能够满足试验件安装和姿态调节需要。传力分析表明该装置的载荷传递方式与真实结构具有高度一致性,其受载状态能够满足缝翼静力试验的验证要求。 In order to meet the requirements of full-scale static test verification of the leading edge slat structure on large passenger aircraft, attitude adjustment devices are designed. The devices are composed of track simulation part, gear simulation part, bearing, bolts, etc. The structures are designed reasonable, which can meet the needs of slat installation and attitude adjustment. Load transfer analysis shows that the load state of the devices is highly consistent with the real structure, which indicating that the devices can meet the requirements of slat static test.
作者 何志全 He Zhiquan(Shanghai Aircraft Design and Research Institute, Shanghai, 201210, China)
出处 《机械设计与制造工程》 2019年第5期60-61,共2页 Machine Design and Manufacturing Engineering
关键词 飞机 缝翼 静力试验 角度调节 aircraft slat static test angle adjustment
作者简介 何志全(1989-),男,工程师,硕士,主要研究方向为飞机结构强度设计与试验验证,hezhiquan@comac.cc.
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