Aircraft Landing Gear of a Dynamic Research and Computer Simulation

2011 ◽  
Vol 383-390 ◽  
pp. 2426-2429 ◽  
Author(s):  
Shen Shou Li ◽  
Xiao Ming Liu ◽  
Zhong Gan Zhu ◽  
Fang Yang
Keyword(s):  
Landing Gear ◽  
Structural Constraints ◽  
Test Results ◽  
Dynamics Model ◽  
Damping Force ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Spring Force ◽  
Adams Software ◽  
Software Modules

by the MSC Adams / Aircraft software features, setting pillar-type landing gear as the prototype, and using ADAMS software modules prior to the establishment of a certain type of aircraft landing gear model, then calculate the air buffer spring force oil, damping force and the structural constraints force curve based on dynamics model, At the end of paper we will analyze the model drop-test results. The results proved that we used this method was feasible.

scholarly journals Intelligent Control Based on a Neural Network for Aircraft Landing Gear with a Magnetorheological Damper in Different Landing Scenarios

2020 ◽  
Vol 10 (17) ◽  
pp. 5962 ◽  
Author(s):  
Quoc Viet Luong ◽  
Dae-Sung Jang ◽  
Jai-Hyuk Hwang
Keyword(s):  
Neural Network ◽  
Mr Damper ◽  
Landing Gear ◽  
Magnetorheological Damper ◽  
Damping Force ◽  
Hybrid Controller ◽  
Aircraft Landing ◽  
Neural Network Controller ◽  
Passive Damper ◽  
Aircraft Landing Gear

A typical oleo-pneumatic shock-absorbing strut (classic traditional passive damper) in aircraft landing gear has a metering pin extending through the orifice, which can vary the orifice area with the compression and extension of the damper strut. Because the metering pin is designed in a single landing condition, the traditional passive damper cannot adjust its damping force in multiple landing conditions. Magnetorheological (MR) dampers have been receiving significant attention as an alternative to traditional passive dampers. An MR damper, which is a typical semi-active suspension system, can control the damping force created by MR fluid under the magnetic field. Thus, it can be controlled by electric current. This paper adopts a neural network controller trained by two different methods, which are genetic algorithm and policy gradient estimation, for aircraft landing gear with an MR damper that considers different landing scenarios. The controller learns from a large number of trials, and accordingly, the main advantage is that it runs autonomously without requiring system knowledge. Moreover, comparative numerical simulations are executed with a passive damper and adaptive hybrid controller under various aircraft masses and sink speeds for verifying the effectiveness of the proposed controller. The main simulation results show that the proposed controller exhibits comparable performance to the adaptive hybrid controller without any needs for the online estimation of landing conditions.

scholarly journals Experimental Validation for the Performance of MR Damper Aircraft Landing Gear

Aerospace ◽  
2021 ◽  
Vol 8 (9) ◽  
pp. 272
Author(s):  
Bang-Hyun Jo ◽  
Dae-Sung Jang ◽  
Jai-Hyuk Hwang ◽  
Yong-Hoon Choi
Keyword(s):  
Numerical Simulations ◽  
Mr Damper ◽  
Absorption Efficiency ◽  
Landing Gear ◽  
Real Time Control ◽  
Damping Force ◽  
Shock Absorption ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Drop Tests

The landing gear of an aircraft serves to mitigate the vibration and impact forces transmitted from the ground to the fuselage. This paper addresses magneto-rheological (MR) damper landing gear, which provides high shock absorption efficiency and excellent stability in various landing conditions by adjusting the damping force using external magnetic field intensity. The performance and stability of an MR damper was verified through numerical simulations and drop tests that satisfied aviation regulations for aircraft landing gear. In this study, a prototype MR damper landing gear, a drop test jig, and a two-degree-of-freedom model were developed to verify the performance of the MR damper, with real-time control, for light aircraft landing gear. Two semi-active control algorithms, skyhook control and hybrid control, were applied to the MR damper landing gear. The drop tests were carried out under multiple conditions, and the results were compared with numerical simulations based on the mathematical model. It was experimentally verified that as the shock absorption efficiency increased, the landing gear’s cushioning performance significantly improved by 17.9% over the efficiency achieved with existing passive damping.

scholarly journals 1002 Aerodynamic noise reduction for aircraft landing gear

2009 ◽  
Vol 2009 (0) ◽  
pp. 321-322
Author(s):  
Kazuhide Isotani ◽  
Kenji Hayama ◽  
Akio Ochi ◽  
Toshiyuki Kumada
Keyword(s):  
Noise Reduction ◽  
Landing Gear ◽  
Aerodynamic Noise ◽  
Aircraft Landing ◽  
Aircraft Landing Gear

A Landing Gear Drop Dynamic Simulation Based on the LMS. Virtual. Lab

2011 ◽  
Vol 55-57 ◽  
pp. 684-687
Author(s):  
Li Zhang ◽  
Cai Jun Xue
Keyword(s):  
Influence Factors ◽  
Landing Gear ◽  
Buffer System ◽  
Air Spring ◽  
Damping Force ◽  
Tire Force ◽  
Virtual Lab ◽  
Spring Force ◽  
Simulation Based ◽  
Fluid Damping

In order to evaluate the dynamic behavior of the buffer of the Seagull 300 aircraft’s main landing gear, a drop model is built to simulate the drop dynamics using the software of LMS Virtual Lab Motion. The fluid damping force of the buffer, the air spring force of the buffer, the tire force of the landing gear and the weight of the fuselage are considered in the model. The simulation results are compared with the results of the Seagull 300 landing gears drop test, which proves the accuracy of the simulation model. Then the buffer performance and its influence factors are computationally discussed. This method gives a new way to study and improve the performance of the buffer system of an aircraft.

Nonlinear Transient Analysis of Aircraft Landing Gear Brake Whirl and Squeal

1995 ◽  
Author(s):  
Matt H. Travis
Keyword(s):  
Finite Element ◽  
Transient Analysis ◽  
Landing Gear ◽  
Friction Modeling ◽  
Explicit Integration ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Nonlinear Transient ◽  
Element Approach ◽  
Stiffness And Damping

Abstract The feasibility of computing non-linear transient finite element simulations of aircraft landing gear brake whirl and squeal is demonstrated and discussed. Methodology to conduct the high frequency brake transient analysis is developed using an explicit integration finite element approach. Results indicate the approach has the capability to simulate brake dynamic behavior in dynamometer and aircraft landing gear installations — thus enabling evaluation of modifications to braking systems that lead to more stable and robust designs. A simple multi-disk brake model is developed and described. Modeling techniques for including the dynamometer road wheel and runway in the simulations are given. Issues such as piston housing hydraulic fluid stiffness and damping effects, and parametric friction modeling are discussed.

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