Optimization of an Oleo-Pneumatic Shock Absorber for Main Landing Gear of a Commercial Aircraft

Patel, Jay S.; Shetty, Drithi; Menghani, Ritika; Barve, S. G.

doi:10.2139/ssrn.3101400

Cited by 3 publications

(2 citation statements)

References 3 publications

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“…For example, the oleo strut, in comparison to alternative landing gears, offers a weight-to-vertical energy dissipation advantage. It consists of a gas chamber producing pneumatic force and features a sharpedged orifice with a conical metering pin structure, including stroke-dependent damping force [2][3][4]. However, achieving high performance under various landing scenarios becomes challenging as the shapes of the orifice and metering pin are predetermined during the design stage.…”

Section: Introductionmentioning

confidence: 99%

Design, structure analysis and shock control of aircraft landing gear system with MR damper

Kang,

Choi

2024

Smart Mater. Struct.

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This study proposes a new Magneto-Rheological Aircraft Main Landing Gear (MRAMLG) system and comprehensively treats from a mathematical modelling to drop testing for the evaluation of the landing efficiency. A mathematical model is formulated based on specifications and requirements of existing small aircrft Oleo type landign gear system. To ensure structural stability of the landing gear components such as main trust, column and trunnion, a transient structural analysis is carried out using the finite element method (FEM) and a fatigue life is analysed based on empirical formulas and the rainflow-counting algorithm.Subsequently, a novel controller is formulated to enhance the landing efficiency by integrating the time delay model and 3-stage hysteresis regulator. In the synthesis of the controller, a desired force model based on the energy law is added to accurately track the desired yield stress needed for the desired field-dependent force. In this work, the proposed control algorithm is named as the model-based force-tracking (MBFT) controller. To evaluate the landing efficiency or shock struct efficiency (SSE) of the proposed MRAMLG, an experimental apparatus for drop test is designed and manufactured by consdiering a dummy (sprung) mass of 640~680 kg at the maximum sink speed of 3 m/s. The sink speed represents the velocity of the MRAMLG’s tire just before it touches the ground. It is demonstrated from simulation and experiment that the SSE with the MBFT controller is higher than 83% across various landing conditions with different sprung mass and sink speed, while the SSE achieved by the proportional-integral (PI) controller and skyhook controller is largely fluctuated depending on the sprung mass and sink speed.

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Section: Introductionmentioning

confidence: 99%

Design, structure analysis and shock control of aircraft landing gear system with MR damper

Kang,

Choi

2024

Smart Mater. Struct.

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“…The landing performance of an aircraft is primarily determined by the landing efficiency, which describes the energy dissipation characteristics of the landing gear (Chartier et al, 2006;Miku1owski and Holnicki-Szulc, 2003: 63-72). In the case of passive landing gear such as the oleo-pneumatic type, the landing performance can be optimized by changing the shape of the metering pin and sharp-edge orifice, depending on the descent rate and strokes of the shock absorber (Li et al, 2017(Li et al, : 1689(Li et al, -1694Patel et al, 2017). Both Roskam and Currey proposed a formula for the shock stroke of the shock absorber, based on aircraft landing efficiency (Daniel, 2011: 861-867;Heerens, 2014).…”

Section: Introductionmentioning

confidence: 99%

Landing efficiency control of a six degrees of freedom aircraft model with magneto-rheological dampers: Part 2—control simulation

Kang

Yoon

Kim

et al. 2020

Journal of Intelligent Material Systems and Structures

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In Part 1 of this work, both the kinematic and dynamic equations of aircraft landing model integrated with magneto-rheological damper were derived. In Part 2, the landing efficiency is analyzed through landing motion simulation which is performed on the basis of the model equations derived in Part 1. To investigate the landing efficiency with respect to the operating force control of magneto-rheological fluid, two different control logics for magneto-rheological damper are designed. The first one is the skyhook controller, which is known to be simple, but very effective for the semi-active control system. In this control logic, the switching condition depending on the compression and extension mode of the damper is determined to achieve maximum energy dissipation. The second one is a modified skyhook controller associated with the semi-active bouncing control. This controller is introduced to prevent bouncing of the main landing gear tires and to reduce the roll motion of the aircraft. The landing efficiency is evaluated at several rates of descent, and its distinct features such as tire displacement and pitch angle are compared in the time domain.

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Overview of Prognostics and Health Management for Landing Gear Maintenance

Haider¹

2019

2019 Annual Reliability and Maintainability Symposium (RAMS)

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Optimization of an Oleo-Pneumatic Shock Absorber for Main Landing Gear of a Commercial Aircraft

Cited by 3 publications

References 3 publications

Design, structure analysis and shock control of aircraft landing gear system with MR damper

Design, structure analysis and shock control of aircraft landing gear system with MR damper

Landing efficiency control of a six degrees of freedom aircraft model with magneto-rheological dampers: Part 2—control simulation

Overview of Prognostics and Health Management for Landing Gear Maintenance

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