Design and Simulation of Semi-Active Landing Gears for Transport Aircraft*

Krüger, Wolf R.

doi:10.1081/sme-120015074

Cited by 32 publications

(31 citation statements)

References 10 publications

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“…It can also shorten the gear life and cause discomfort to the pilot and passengers. the stretching of existing aircraft, see [11], and the use of new, light-weight structures and materials that influence the vibrational properties of fuselage and wings. Not only unsuitable combination of structural stiffness, damping, and pneumatic tire characteristics but also an unlucky combination of brake system design with the tire physics can produce a serious vibration problem [14].…”

Section: Landing Gear Dynamics -Problem Definitionmentioning

confidence: 99%

Gear walk instability studies using flexible multibody dynamics simulation methods in SIMPACK

Khapane

2006

Aerospace Science and Technology

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Section: Landing Gear Dynamics -Problem Definitionmentioning

confidence: 99%

Gear walk instability studies using flexible multibody dynamics simulation methods in SIMPACK

Khapane

2006

Aerospace Science and Technology

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“…His thesis also includes a comprehensive list of references concerning the topic [15]. Vibration reduction of landing gear by active shock absorbers, including dynamic modelling of the landing gear, has been investigated by several authors, among others, Krüger [16] and Sateesh [17]. Recent publications on nonlinear dynamics of landing gear, including stability and bifurcation analysis, and related to the approach presented in Sect.…”

Section: Available Literaturementioning

confidence: 99%

Recent developments at the numerical simulation of landing gear dynamics

Krüger

Morandini

2011

CEAS Aeronaut J

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Aircraft landing gears support the aircraft during ground operations, including take-off, landing impact, taxiing, gate handling and maintenance. Mostly for reasons of minimum mass and ground clearance, landing gears are slender structures which exhibit a considerable dynamic response to ground load excitations. As the landing gear is one of the few systems on the aircraft without redundancies, the knowledge of landing gear dynamics is crucial for aircraft design and aircraft safety. Simulation of landing gear dynamics is a cornerstone of aircraft loads analysis, as well for vertical loads resulting from touch-down as for longitudinal and lateral loads resulting from braking, steering and towing. Another important field of interest is landing gear vibrations like gear walk and shimmy. Those phenomena can be brake induced or result from tire spin-up at touchdown or simply from a coupling of dynamics of the running tire and structural mechanics of the landing gear leg. All those effects strongly depend on a number of parameters such as aircraft speed, landing gear vertical deflection, tire pressure and wear of the parts. Many of those parameters can only be estimated and might change during the operation of the aircraft. Numerical investigation is thus a challenging task. Analysis methods exist both in the frequency domain and in the time domain. As stability analysis is straight forward in frequency domain methods, this approach is still often used. However, in many cases nonlinearities are dominant which lead to limit-cycle characteristics of the vibrations. Here, multibody modelling or a mixture of multibody and finite element modelling including time domain simulation is used. In the article, a general outline is given of how vibration problems in landing gears can be treated by numerical analysis methods. The article will start with a classification of typical problems, give a short overview of classical papers, and explain typical approaches. In addition, alternative approaches for stability analysis and for the detection of limit-cycle oscillations as well as state-ofthe-art modelling approaches will be presented.

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“…그러나, 최신 유공압 완충 형까지 고려된 착륙장치는 모두 수동형으로써, 성능향상의 한계성, 다양한 설계운용조건에서 최 적성능 구현의 어려움 등으로 본 논문과 같이 반 능동제어 착륙장치가 연구되고 있다 [2,3].…”

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Force Control of Main Landing Gear using Hybrid Magneto-Rheological Damper

Hyun¹,

Hwang²,

Hwang³

et al. 2010

Journal of the Korean Society for Aeronautical Space Science

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To improve not only the basic performance but also the fail-safe performance, power consumption of the main landing gear for helicopters, a semi-active control landing gear using hybrid MR damper, was introduced in this paper. This damper of the configuration to install a permanent magnet in a electromagnet MR damper, was designed by the trade-off study on permanent magnet location and a magnet field analysis. Force control algorithm which keep the sum of air spring force and damping force at a specified value during landing, was used for the controller. The drop simulations using ADAMS Model for this semi-active control landing gear, were done. The improvement of the preceding performances as the result to evaluate the landing performance by the simulations, has been confirmed.

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Design and Simulation of Semi-Active Landing Gears for Transport Aircraft*

Cited by 32 publications

References 10 publications

Gear walk instability studies using flexible multibody dynamics simulation methods in SIMPACK

Gear walk instability studies using flexible multibody dynamics simulation methods in SIMPACK

Recent developments at the numerical simulation of landing gear dynamics

Force Control of Main Landing Gear using Hybrid Magneto-Rheological Damper

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