THE FATIGUE ANALYSIS OF HELICOPTER HUB BASED ON FE-SAFE
Helicopter hub receives the centrifugal force of rotor blade which transfers from blade root. At the same time, it must support the flapping and lagging force of blade. So the load applying to hub is complex and the stress is alternating. Thus, the combined load and the cyclic stress can lead blade hub to fatigue failure. In this paper, the load of helicopter hub has been described and the stress has been computed. With this static stress and a random loadspectrum which considered different flight condition about helicopter, the fatigue analysis of hub based on FE-SAFE software has been carried out. The treatment of fatigue load spectrum in this paper represents not only hovering flight condition but also anther flight condition such as level and forward flight. Furthermore, the flight test result has proved that the solution method of hub’s life is feasible and the fatigue life is correct.
Nianzhao Jiang Hui Chen Yong Dai Zhiqing Zhang Kexuan Wang Hongbo Wu Jinping Tao
The Research Institute of Simulation Technology of Nanjing, No. 2 Huangpu Street, Nanjing,210016, P. Ansys-China Shanghai Office. Room 801, Aurora International Building 99 Fucheng Rd.Shanghai,200120,
国际会议
第九届工程结构完整性国际会议(The Ninth International Conference on Engineering Structural Integrity Assessment)
北京
英文
2007-10-15（万方平台首次上网日期，不代表论文的发表时间）