Bifurcation Analysis of a Nose Landing Gear System

Failure propagation is a critical factor for the reliability and safety of complex systems. To recognise and identify failure propagation of systems, a deep fusion model based on deep belief network (DBN) and Bayesian structural equation model (BSEM) is proposed. The deep belief network is applied to extract features between status monitoring data and the performance degradation in different failure components. To calculate the path weight of failure propagation, the Bayesian structural equation model is proposed to study the relationship among different fault modes. After getting the performance degradation of each fault through DBN and calculating the path weight of fault propagation by BSEM, it is available to get the overall reliability of the system. The aircraft landing gear system with 19 fault patterns is selected to evaluate the feasibility of the proposed deep fusion model. The results demonstrate that the overall reliability of the system can be obtained by analysing the fault propagation of multiple fault patterns, and the proposed model has a lower deviation than traditional back propagation neural network.

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“…An aircraft landing gear system as shown in Fig. 4 is a typical complex system with numerous components 22 .…”

Section: Case Studymentioning

confidence: 99%

Reliability Analysis of Complex Systems with Failure Propagation

Che

Wang

2019

Def. Sc. Jl.

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“…The validation considers the occurrence of shimmy phenomena in landing gear systems during ground manoeuvres [29,35,36]. Shimmy results from the nonlinear interaction between the follower forces acting on the tyre and the modes of vibration, resulting in Limit Cycle Oscillations (LCOs).…”

Section: Case Study and Bifurcation Analysismentioning

confidence: 99%

Enhanced Evolutionary-Based Optimization Techniques Applied to a Nonlinear Landing Gear Design Problem

Tartaruga

Cooper

Löwenberg

et al. 2019

Journal of Aircraft

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Engineering design processes often use optimization strategies, which aim to minimize multi-objective functions. The analysis should consider the uncertainty in a system, which may cause signicant changes in its behaviour. The inclusion of the uncertainty in the design process makes the identication of an optimum design more challenging. In this paper, two novel optimization methods (Iterative Dierential Evolutionary Algorithm-I.D.E.A. and Reliable & Robust Evolutionary Algorithm-R.R.E.A.) are presented. These optimization strategies aim to solve problems that are very time demanding and for which it is dicult (and expensive) to determine derivatives and to identify and dene the optimum set of parameters. The approaches are validated considering as a test case the optimization of a landing gear system in order to avoid the onset of shimmy, assuring a reliable design.

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“…Somieski [4] applied wellknown linear mathematical methods to analyzing the shimmy of a basic nose landing gear model and investigated the impact of various structural parameters on the shimmy dynamics. Tartaruga [5] performed sensitivity and uncertainty analysis using singular value decomposition to investigate the impact of various structural parameters on shimmy onset. The results indicate that the proposed method reduces the computational time compared to full-scale full element simulation.…”

Section: Introductionmentioning

confidence: 99%

Research on the Stability and Bifurcation Characteristics of a Landing Gear Shimming Dynamics System

Ruan,

Zhang,

Yang

et al. 2024

Aerospace

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A dynamic model is established to investigate the shimmy instability of a landing gear system, considering the influence of nonlinear damping. The stability criterion is utilized to determine the critical speed at which the landing gear system becomes unstable. The central manifold theorem and canonical method are employed to simplify the dynamic model of the landing gear. The first Lyapunov coefficient of the system is theoretically derived and verified using numerical simulation. Further investigation on the Hopf bifurcation characteristics and stability of the shimmy in the landing gear system is conducted. The results indicate that above a certain threshold speed, with a tire stability distance greater than half the tire length in contact with the ground plus the slack length, the aircraft remains stable during taxiing. At critical speeds, a shimmy system with higher-order nonlinear damping will undergo supercritical Hopf bifurcation. Quantitative analysis suggests an increase in the linear damping coefficient within a range that ensures a stability margin to mitigate undesired oscillation, while the nonlinear damping coefficient should be designed within a reasonable range to decrease the amplitude of the limit cycle.

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Bifurcation Analysis of a Nose Landing Gear System

Cited by 9 publications

References 12 publications

Reliability Analysis of Complex Systems with Failure Propagation

Reliability Analysis of Complex Systems with Failure Propagation

Enhanced Evolutionary-Based Optimization Techniques Applied to a Nonlinear Landing Gear Design Problem

Research on the Stability and Bifurcation Characteristics of a Landing Gear Shimming Dynamics System

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