Optimization of landing gear under consideration of vibration comfort for civil aircraft

Abstract

Purpose

This study aims to investigate the design and optimization of landing gear buffers to improve the landing-phase comfort of civil aircraft.

Design/methodology/approach

The vibration comfort during the landing and taxiing phases is calculated and evaluated based on the flight-testing data for a type of civil aircraft. The calculation and evaluation are under the guidance of the vibration comfort standard of GB/T13441.1-2007 and related files. The authors establish here a rigid-flexible coupled multibody dynamics finite element model of one full-size aircraft. Furthermore, the authors also implement a dynamic simulation for the landing and taxiing processes. Also, an analysis of how the main parameters of the buffers affect the vibration comfort is presented. Finally, the optimization of the single-chamber and double-chamber buffers in the landing gear is performed considering vibration comfort.

Findings

The double-chamber buffer with optimized parameters in landing gear can improve the vibration comfort of the aircraft during the landing and taxiing phases. Moreover, the comfort index can be increased by 25.6% more than that of a single-chamber type.

Originality/value

To the best of the authors’ knowledge, this study first investigates the evaluation methods and evaluation indexes on the aircraft vibration comfort, then further conducts the optimization of the parameters of landing gear buffer with different structures, so as to improve the comfort of aircraft passengers during landing process. Most of the current studies on aircraft landing gear have focused on the strength and safety of the landing gear, with very limited research on cabin vibration comfort during landing and subsequent taxiing because of the coupling of runway surface unevenness and airframe vibration.

Citation

Yan, S., Xue, P., Liu, L. and Zahran, M.S. (2024), "Optimization of landing gear under consideration of vibration comfort for civil aircraft", Aircraft Engineering and Aerospace Technology, Vol. 96 No. 3, pp. 378-386. https://doi.org/10.1108/AEAT-05-2023-0130