Parametric study of a novel nose landing gear shimmy damper concept

Rahmani, Mohsen; Behdinan, Kamran

doi:10.1016/j.jsv.2019.06.008

Cited by 17 publications

(13 citation statements)

References 27 publications

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“…The shimmy damper and the strut's torsional stiffness are connected in parallel, and the parallel stiffness is then connected in series with the sliding tube's torsional stiffness. Equation (2)(3)(4)(5)(6)(7)(8)(9)(10)(11) displays the analogous relationship between the torsional damping of the two models. The sliding tube damping, the shimmy damper damping, and the main fitting damping are coupled in series.…”

Section: Mathematical Modeling Of Three Torsional Degrees Of Freedom ...mentioning

confidence: 99%

“…The lateral force of the left and right wheels is shown in Equations (2)(3)(4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15).…”

Section: Mathematical Modeling Of Stretched String Tirementioning

confidence: 99%

“…Inadequate torsional damping, old tires, and structural components, insufficient caster length, excessive torsional clearance, and other issues contribute to the nose landing gear shimmy [2][3][4][5][6][7][8]. Engineers typically utilize landing gear dampers to improve the system's torsional damping to reduce shimmy [9][10][11][12][13][14]. In addition, research on controlling shimmy vibration has been done recently.…”

Section: Introductionmentioning

confidence: 99%

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Influence of structural torsional degree of freedom on nose landing gear shimmy

Ding,

Feng,

Liu

et al. 2023

Preprint

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The structural characteristic of combining a maneuvering mechanism and a shimmy damper into a single component is present in the nose landing gear of large civil aircraft. Establishing a more accurate shimmy model based on this property is crucial. The three torsional degrees of freedom shimmy of the nose landing gear was mathematically and physically modeled. The time domain curve, spectrum diagram, and bifurcation diagram were used to compare the three torsional degrees of freedom shimmy model and the single torsional degrees of freedom shimmy model. The three-torsional freedom model predicts a greater amplitude and a longer convergence time in comparison to the findings of the single-torsional freedom model. The sliding tube's torsional vibration frequency falls from 10.9Hz to 8.1Hz in the three-torsional degree-of-freedom model, while the structure's lateral vibration frequency stays the same. The three-torsional freedom model predicts a decrease in the region of stable and torsional shimmy and an increase in the area of lateral and quasi-periodic shimmy. The amplitudes of all degrees of freedom in the three torsional degrees of freedom model, regardless of whether it is torsional or lateral, are greater than those in the single torsional degrees of freedom model when the vertical load is fixed. By increasing the torsional degrees of freedom of the shimmy damper and the main fitting, the inertia, stiffness, and damping in the torsional direction are redistributed in the three-torsional shimmy vibration model, which reduces the stability of the system.

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Section: Mathematical Modeling Of Three Torsional Degrees Of Freedom ...mentioning

confidence: 99%

“…The lateral force of the left and right wheels is shown in Equations (2)(3)(4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15).…”

Section: Mathematical Modeling Of Stretched String Tirementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Influence of structural torsional degree of freedom on nose landing gear shimmy

Ding,

Feng,

Liu

et al. 2023

Preprint

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“…Currently, research on aircraft ground movement characteristics, both domestically and internationally, primarily focuses on linear motions such as landing deceleration, runway shock absorption, and yaw oscillations [1][2][3][4][5][6][7] . There is relatively less research concerning civil aircraft's taxiing, turning, or lateral movements on the runway.…”

Section: Introductionmentioning

confidence: 99%

Analysis and study of maximum allowable turning speed for civil aircraft

Feng,

Pan,

Zhao

et al. 2024

J. Phys.: Conf. Ser.

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The maximum allowable turning speed of an aircraft is a critical factor affecting the safety of civil aviation. Evaluating the maximum permissible taxiing turn speed for civil aircraft is an essential aspect of aircraft design. To ensure that the aircraft does not experience unbalanced forces leading to a lateral rollover due to excessive taxiing speed, an engineering estimation method is employed to study the maximum permissible taxiing turn speed for civil aircraft. This method begins with certain assumptions and calculation scenarios, followed by the derivation of a calculation model based on the analysis of aircraft forces. Lastly, a case study of a specific aircraft’s maximum taxiing turn speed is conducted in conjunction with practical engineering considerations. The study reveals that as crosswind forces on civil aircraft increase, the maximum turning speed decreases. Moreover, for lighter aircraft with a forward center of gravity, the risk of lateral rollovers is higher. These findings underscore the engineering applicability of the estimation method.

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“…The shimmy of the NLG will seriously affect the stability of the body and the ride comfort and aircraft operation, cause damage to the body and landing gear and endanger the safety of life and property. There are numerous factors affecting the shimmy of the NLG, including linear and nonlinear factors, which can be summarized into four parts: NLG structural characteristics [6][7][8][9][10], wheel characteristics [11][12][13], fuselage characteristics [14][15][16] and external conditions [17][18][19]. Among them, the structural clearance has strong nonlinearity and discontinuity, which makes the dynamic behavior of the system very complicated, and it also causes great difficulties to the vibration analysis of the landing gear system and the practical application of the analysis conclusions.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Joint Clearance Effects on the Shimmy of Nose Landing Gear

Jiang,

Feng,

Liu

et al. 2023

Aerospace

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Through the establishment of a three-dimensional joint clearance model, the effects of joint clearances at different positions on shimmy stability are evaluated. In this paper, considering the radial, axial and coupling characteristics of joint clearance, the shimmy multibody dynamics (MBD) model is applied to different joints in the nose landing gear (NLG) transmission system. It is proposed to evaluate the influence of joint clearance on shimmy from two aspects of position factor and wear factor. The study found that different joint clearances have different effects on shimmy: the joint clearance between the NLG and fuselage has little influence on shimmy; the larger axial clearance of upper and lower torque link joint will cause the shimmy of the NLG, but the radial clearance has no effect on shimmy; while the joint clearance between turning sleeve and upper torque link, lower torque link and piston only works in the axial and radial coupling. The reasons for the different influence characteristics of each joint space are analyzed. Consequently, studying and summarizing the influence of different clearance on shimmy is of great significance for the design and maintenance of the NLG joints.

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Parametric study of a novel nose landing gear shimmy damper concept

Cited by 17 publications

References 27 publications

Influence of structural torsional degree of freedom on nose landing gear shimmy

Influence of structural torsional degree of freedom on nose landing gear shimmy

Analysis and study of maximum allowable turning speed for civil aircraft

Evaluation of Joint Clearance Effects on the Shimmy of Nose Landing Gear

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