Open Access
Analysis of Landing-Gear Behavior
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In this article, a theoretical study of the behavior of the conventional oleo-pneumatic landing gear during the process of landing impact is presented in a general form and treats the motions of the landing gear prior to and subsequent to the beginning of shock-strut deflection.Abstract:
This report presents a theoretical study of the behavior of the conventional type of oleo-pneumatic landing gear during the process of landing impact. The basic analysis is presented in a general form and treats the motions of the landing gear prior to and subsequent to the beginning of shock-strut deflection. The applicability of the analysis to actual landing gears has been investigated for the particular case of a vertical landing gear in the absence of drag loads by comparing calculated results with experimental drop-test data for impacts with and without tire bottoming. The calculated behavior of the landing gear was found to be in good agreement with the drop-test data.read more
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Proceedings ArticleDOI
Modeling and Validation of an Oleo-Pneumatic Damper with Mechatronic Subsystems for CS-23 General Aviation Aircraft
TL;DR: In this article , the authors deal with common modeling methods of an oil-pneumatic damper for CS-23 general aviation aircraft with extended mechatronic subsystems and show their as-sumptions and physical transferability.
Proceedings ArticleDOI
Equations of State in Fighter Aircraft Oleo-pneumatic Shock Absorber Modelling
Abstract: Most of all modern commercial and military aircraft have oleo-pneumatic shock absorbers in their landing gear. An oleo-pneumatic shock absorber consists of a gas charge and an oil fill. During the stroke oil is forced through orifices which provides damping, while the gas charge is compressed and acts as a spring by increasing the stiffness of the shock absorber. Typically, when the gas behaviour is modelled, the ideal gas law is used as the equation of state as this provides in most cases adequate fidelity with relatively light computational load. However, in a fighter aircraft, especially in naval service, the gas pressure inside a shock absorber raises too high during landing for the ideal gas assumption to be valid. Therefore, other well-established equations of state have been considered. These are Van der Waals, RedlichKwong-Soave, and Peng-Robinson equation of state. This paper presents a multi-physics simulation model of a two-chamber oleo-pneumatic shock absorber based on fundamental analytical equations. Using this model, the behaviour of the aforementioned equations of state are studied in two cases: quasi-static and dynamical compression. The simulation results are compared to laboratory measurements. This comparison verifies that the ideal gas law should not be used when modelling naval fighter aircraft shock absorbers.
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Proceedings ArticleDOI
Dynamic Modeling of the Aircraft Landing Gear Based on ISD Mechanism
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Influence of friction forces on the motion of VTOL aircraft during landing operations on ships at sea
J. C. Howard,D. O. Chin +1 more
TL;DR: In this article, a set of relatively simple equations were obtained by including only those tire and shock strut characteristics that contribute significantly to the generation of landing gear forces, and simplifications were introduced to reduce the complexity of the mathematical description of the tire and strut characteristics.