Dynamic Response of an Aircraft Flap Reducer

• Main Authors: Tsai Ming Hwn, 蔡銘湖
• Other Authors: Kuang Jao-Hwa
• Format: Others
• Language: zh-TW
• Published: 1998
• Online Access: http://ndltd.ncl.edu.tw/handle/40256121329338987406

碩士 === 國立中山大學 === 機械工程研究所 === 86 === An aircraft flap gear reducer with an auxiliary power supply system is studied in this thesis. The dynamic model for the aircraftflap gear reducer system is developed by employing Lagrange's equation.Dynamic responses of the system is solved by using the Runge-Kuttamethod. The torsional vibration of the gear system in a completeoperating cycle, i.e., start, accelerate, decelerate, and stop hasbeen investigated. Both the transient and the steady-state responses are studied. Emphasis is focused on the interaction between the gear train system and the driving motor. The effect of the meshstiffness on the dynamic responses of the engaging gear pairs is alsoconsidered. A two-step mesh stiffness model is used in the dynamicmodel to emphasize the characteristics of the time varying mesh stiffness. Corresponding frequency spectra of the flap gear reducer system has also been studied.