To further clarify the interaction mechanisms and dynamic responses within the aircraft-runway system, a physical

model of the dynamic interaction between the aircraft main landing gear and and rigid runway was developed firstly,

and the aircraft tire and runway foundation were simulated as rigid roller model and Pasternak foundation model,

respectively. Secondly, mathematical expressions of rigid roller model and Pasternak foundation model were derived based on the principle of displacement coordination, and a novel fast explicit integration algorithm was employed to solve the vibration response of both the aircraft landing gear and the runway structure. Finally, taking the

B737-800 aircraft as a case study, the dynamic responses of the aircraft subsystem and runway subsystem were analyzed under different runway structural strengths, aircraft taxiing speeds and pavement roughness to reveal the key

factors influencing aircraft safety, comfort degree and runway structure safety. The results indicated that the attenuation of the foundation stiffness has a great influence on the runway vibration response, with a maximum growth rate

of 56.13%. As the aircraft taxiing speed increases, the vibration displacement peak of the lower pavement of the

wheel initially rises and then falls, while the vibration acceleration peak of both the fuselage and wheels consistently increase. Due to the dissipation effect of the landing gear buffer, the influence of runway roughness on fuselage vibration acceleration has a lag effect.

airport engineering, vibration response, system dynamics, aircraft landing gear, rigid runway