Research on the Performance of an Aircraft Landing Gear Hook Lock Based on Bifurcation Analysis
College of Aerospace Engineering, State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
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Appl. Sci. 2019, 9(24), 5278; https://doi.org/10.3390/app9245278
Received: 28 October 2019 / Revised: 17 November 2019 / Accepted: 30 November 2019 / Published: 4 December 2019
(This article belongs to the Section Mechanical Engineering)
To design and analyze a hook lock mechanism for a certain type of aircraft landing gear, numerical continuation and bifurcation theory are employed to study the performance of the lock mechanism in this paper. First, dynamic and static models of the hook lock mechanism are created separately, and by analyzing the locking and unlocking processes of the lock mechanism, the dynamic results are compared with the static numerical continuation results. According to the results, the static numerical continuation results agree excellently with the dynamic model results at the position of the stable equilibrium solution. Although the dynamic results can hardly explain the jump phenomenon of the lock mechanism at the moment of locking or unlocking, the bifurcation point of the static results suggests the occurrence of a stability change in the lock mechanism at the moment of jumping, thereby explaining the jumping mechanism of the lock mechanism. Therefore, the influences of the landing gear overload, lock spring parameters and attachment position on the performance of the lock mechanism are investigated. Furthermore, the critical installation position of the limit stop is defined, and the critical unlocking force of the lock mechanism is designed optimally based on the multi-island genetic algorithm.
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MDPI and ACS Style
Yin, Y.; Xu, K.; Nie, H.; Wei, X.; Zhang, Z. Research on the Performance of an Aircraft Landing Gear Hook Lock Based on Bifurcation Analysis. Appl. Sci. 2019, 9, 5278.
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