Effect of clearance position of torque link structure on nose landing gear shimmy

Gao, Xiangguo; Zheng, Yuchen; Du, Xiaolei; Shan, Zezhong; Jia, Baohui; Lu, Xiang

doi:10.1016/j.ijnonlinmec.2023.104616

Cited by 4 publications

(2 citation statements)

References 16 publications

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“…The Figure7 presents the landing configuration, depicting the imminent contact between the nose gear and the ground. The measurements a, b, and d were obtained from the Twin-Otter data book, enabling the determination of a', b', and d'-while inclined (Currey, 1988;Federal Aviation Authority's [FAA], 2011;Gao et al, 2024;Hagins et al, 2007;Liang et al, 2022). Where, K = 0.33; for 𝑊𝑙𝑎𝑛𝑑𝑖𝑛𝑔 > 6,000 𝑙𝑏𝑠 Subsequently, we get (FAA, 2011) from Figure 7;…”

Section: Numerical Simulationmentioning

confidence: 99%

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Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Yadav,

Sudhakar

2023

Orchid Acad. Siraha

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Landing gear failures are a major cause of aircraft failures because they are an integral part of the aircraft's development. According to the Federal Aviation Administration (FAA), 50% of all aircraft failures occur during take-offs and landing. The landing gear of a short take-offs and landing (STOL) aircraft has had its static and dynamic forces analyzed analytically and numerically. SOLIWORKS is used to model the landing gear, and ANSYS is used to perform the numerical simulation results. Following it, the model is examined for stress and deformation with the boundary conditions and computed loads into account. This study uses structural finite element analysis (FEA) to analyze the nose gear's stress behavior and displacement during landing, as well as to assess the effect of the runway gradient. Utilizing a comprehensive numerical simulation, the landing gear of a real material Twin-Otter STOL aircraft has been demonstrated to be subjected to a dynamic force of 3653.26N, a pneumatic pressure of 1.59MPa, a bead pressure of 7.97MPa, and a vertical force of 1672.31lbs on level runways, or runways with no gradient. These findings will increase the level of confidence of aircraft manufacturers to make necessary appropriate design of STOL aircraft’s landing gear. It may can decrease the aircraft accidents and increase human life safety ultimately saving valuable time and resources too.

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Section: Numerical Simulationmentioning

confidence: 99%

“…The required formula for the conversion is: Pneumatic Pressure. The initial air pressure, the area exposed to the air pressure, and the compression ratio, as described by the polytropic law for gas compression given below (Gao et al, 2024;Schmidt, 2021;Sonowal et al, 2021):…”

Section: Numerical Simulationmentioning

confidence: 99%

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Yadav,

Sudhakar

2023

Orchid Acad. Siraha

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Shimmy performance analysis and parameter optimization of a dual-wheel nose landing gear coupled with torsional nonlinear energy sink and considering structural nonlinear factor

Wang,

Zhang,

Bian

et al. 2024

Chaos, Solitons & Fractals

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Dynamics analysis of nose landing gear shimmy performance considering aircraft structural flexibility

Ruan,

Zhang,

Yang

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study examines the sliding vibration characteristics of high-speed aircraft constructed with multi-layer composite materials and designed with a large cabin opening, which consequently leads to diminished overall structural integrity and lower natural vibration frequencies. To assess the influence of structural flexibility on the shimmy behavior of the nose landing gear during taxiing, a rigid-flexible coupling dynamic model was developed based on multi-body dynamics theory, integrating considerations of structural flexibility. The modal stiffness derived from this model was compared to that obtained from a finite element analysis, and simulations were performed to evaluate shimmy stability. The results reveal that fuselage motion enhances the damping coefficient for anti-shimmy while concurrently decreasing the oscillation frequency. When the structural frequency approaches the oscillation frequency, the stability of the system may be jeopardized. Therefore, it is crucial to prevent the alignment of the landing gear’s shimmy frequency with the structural frequency during the design process. Excessive flexibility in the fuselage can result in substantial lateral deformation, which disrupts the normal vibration pattern of the wheels’ angular motion and reduces the system’s capabilities for anti-shimmy and sliding control. Furthermore, when the fuselage demonstrates significant flexibility, the influence of the nose section on shimmy becomes pronounced, indicating that employing earpieces to simulate the body’s stiffness for shimmy analysis is not a suitable approach.

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Effect of clearance position of torque link structure on nose landing gear shimmy

Cited by 4 publications

References 16 publications

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Shimmy performance analysis and parameter optimization of a dual-wheel nose landing gear coupled with torsional nonlinear energy sink and considering structural nonlinear factor

Dynamics analysis of nose landing gear shimmy performance considering aircraft structural flexibility

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