Spectrum parameters for runway roughness based on statistical and vibration analysis

Qian, Jiangu; Cen, Yebo; Pan, Xiangwei; Tian, Yu; Liu, Shifu

doi:10.1080/10298436.2021.1916821

Cited by 2 publications

(2 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…where q( f , t) is virtual excitation; and G q ( f ) is the power spectral density (PSD) model for asphalt runway roughness; e is a constant of nature; i is an imaginary number; and f is the frequency. Under virtual excitation, the virtual response of the whole system is calculated according to Equation (19):…”

Section: Pseudo Excitation Methods Used For Calculationsmentioning

confidence: 99%

“…Because an aircraft is sensitive to both long-and short-wave unevenness of the runway, the excitation form of the unevenness of the runway should be different from that of a road surface [17]. Qian et al proposed spectrum parameters for runway roughness evaluation via measurements of full-width band data obtained for a Chinese airport runway [18,19]. Adopting the Sussman model as the PSD model for asphalt runway roughness, the power spectrum for runway roughness is shown in Equation ( 22):…”

Section: Runway Uneven Excitation Inputmentioning

confidence: 99%

See 1 more Smart Citation

Random Vibration Analysis of a Coupled Aircraft/Runway Modeled System for Runway Evaluation

et al. 2022

Self Cite

View full text Add to dashboard Cite

Runway roughness is one of the most critical performance factors for runway evaluation, which directly impacts airport operation safety and pavement preservation cost. Properly evaluated runway roughness could optimize the decision-making process for runway preservation and therefore reduce the life cycle cost of the runway pavement asset. In this paper, the excitation effect of runway roughness is analyzed using a coupled aircraft/runway system. The coupled system is composed of a two degrees-of-freedom (2-DOF) aircraft model and a typical asphalt runway structure model established under runway roughness random excitation in this work. The dynamic differential equations for the coupled system are derived based on D’Alembert’s principle. The system’s vibration responses are determined via the pseudo excitation method and three response laws, i.e., the center of gravity acceleration (CGA), the dynamic load coefficient (DLC) of the landing gear, and the runway structural displacement, which are investigated under different modes. The results show that the first-order mode of the runway structure, vertical deformation, is the most significant of the four modes. Moreover, uneven excitation has a significant effect on the distribution of the aircraft’s vibration response. Compared with a single aircraft system, the developed coupled aircraft/runway system has different dynamic responses, and the degree of difference depends on the taxiing speed. The coupled effect on the CGA increases significantly with an increase in speed, with up to a 7.3% percentage difference. The coupled effect on the DLC first increases and then decreases as the aircraft speed increases, reaching a maximum of about 6% percentage difference at 120 km/h.

show abstract

Section: Pseudo Excitation Methods Used For Calculationsmentioning

confidence: 99%

Section: Runway Uneven Excitation Inputmentioning

confidence: 99%