Landing Gear Structural Health Monitoring (SHM)

Forrest, C. F.; Forrest, Clint; Wiser, Doug

doi:10.1016/j.prostr.2017.07.025

Cited by 8 publications

(9 citation statements)

References 1 publication

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“…Indeed, the contemporary use of other types of sensors allows further independent comparisons of the achieved results, increasing their confidence. Such lab tests are therefore carried out in a very different environment with respect to the operational one, coherent with the TRL of this phase of investigation (3)(4). Accordingly, a typical laboratory bonding process is used, coherent with other different experiments, and performant enough to replicate actual adhesion quality in that environment.…”

Section: Fbgs and Sgs Arraysmentioning

confidence: 99%

“…Such kinds of monitoring systems can be also used for the assessment of system vibrations, which may include self-induced and brake-induced oscillations. The aircraft industry and researchers have dedicated many efforts in developing techniques and methods devoted to the measurement of operational loads and have elaborated proper processes for flyable hardware architectures overcoming many obstacles [4][5][6]. Within the following paper, a short bibliography summary of a number of the prevailing solutions for landing gear loads monitoring, for various purposes, is reported.…”

Section: Introductionmentioning

confidence: 99%

“…Another one implements laser deflection measurement devices, mounted on an axle and made of light emitting and receiving systems [14]. Direct load measurement can be performed via instrumented load pin [4,13]. A harsh landing event recorder for helicopter condition-based maintenance implementing a capacitive transducer was proposed in [15].…”

Section: Introductionmentioning

confidence: 99%

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A Preliminary Assessment of an FBG-Based Hard Landing Monitoring System

et al. 2021

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In aeronautics, hard landing is a critical condition as the aircraft approaches the runway with a vertical velocity that exceeds 2 m/s. Beyond that level, the energy that should be then absorbed by the whole structure could cause severe damage to the landing gear and the whole structural system. This document reports on the set-up, execution and results of a preparatory test campaign performed on a small landing gear (LG) demonstrator instrumented with a fibre-optic sensor system. In detail, a leaf spring landing gear was released from a drop tower to detect information about the strain state and the related acceleration history of some specific components during the impact. The objective of the present research is the development of a method for assessing whether hard landing is experienced, and to what extent. Deformation measurements through an integrated Fibre-Bragg grating (FBG) network allowed retrieving impact velocity by a devoted, original algorithm. The proposed preliminary methodology is the base for assessing a more complex procedure to correlate structural response to the energy entering the structure during the touchdown event.

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Section: Fbgs and Sgs Arraysmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A Preliminary Assessment of an FBG-Based Hard Landing Monitoring System

et al. 2021

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“…Aircraft industry and research have dedicated many efforts in developing both suitable load measurement techniques and methods, and proper processes for flyable hardware architectures overcoming many showstoppers. [5][6][7] In the following, the authors report a bibliography scenario overviewing some of the existing solutions for landing gear loads monitoring, for different objectives.…”

Section: Introductionmentioning

confidence: 99%

Landing gear hard impact: Preliminary study on optic monitoring system

Brindisi

Vendittozzi

Travascio

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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With the prospective of developing an integrated monitoring system aimed at assessing whether a landing gear has experienced hard impact during the approach, a dedicated method is developed aimed at determining vertical speed by means of strain measurement via FBG strain sensors. Representative impacts on simple structural elements have been reproduced in laboratory, as aluminum slender beams of different lengths were dropped from given heights onto a steel plate base. Contact velocities have been estimated by deformations detection.

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“…The current aircraft fatigue loading test urgently needs to shorten the time: It takes 2 to 6 years [ 5 ] to complete. Because the average life of modern civil aircraft is as high as 60,000 flight hours multiple life tests are required in the test [ 6 , 7 ]. The key to influencing the test time now is the limitation of the loading frequency and the strong coupling between the channels [ 8 , 9 ].…”

Section: Introductionmentioning

confidence: 99%

Motion Synchronous Composite Decoupling with Fewer Sensors on Multichannel Hydraulic Force Control for Aircraft Structural Loading Test System

Bai

Jiao

Yao

et al. 2018

Sensors

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The aircraft full-scale fatigue test is widely used in the modern aircraft industry for the safety of flight. Generally, the aircraft full-scale fatigue test is achieved by structural loading; multiple hydraulic actuators are used to apply load for force control. The fatigue loading test takes approximately several years. A key challenge is how to accelerate the loading frequency to shorten the total test time. Nevertheless, when pluralities of hydraulic actuator simultaneously increase the loading frequency, the mutual coupling force from the low rigidity of the aircraft structure will cause a large loading error, meaning that the test cannot be implemented. Although it is possible to reduce error by adding sensors, the force sensors need to connect several kilometers of cable. This paper proposed a novel motion synchronous composite decoupling control strategy with fewer sensors. The control method compensates the negative coupling effect of the channels by integrating the command signals and feedback signals of all channels. It can suppress coupling force and reduce errors at higher frequencies, thereby shortening the experiment time. Opposed to traditional decoupling control methods, advantages of this strategy are that it only needs force sensors and it does not need additional displacement or velocity and acceleration sensors to collect state variables for building the state space. Furthermore, it has been experimentally verified that the new motion synchronous composite decoupling control method can indeed guarantee sufficient control accuracy when the test frequency is increased. The method has great economic significance for shortening test duration.

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Landing Gear Structural Health Monitoring (SHM)

Cited by 8 publications

References 1 publication

A Preliminary Assessment of an FBG-Based Hard Landing Monitoring System

A Preliminary Assessment of an FBG-Based Hard Landing Monitoring System

Landing gear hard impact: Preliminary study on optic monitoring system

Motion Synchronous Composite Decoupling with Fewer Sensors on Multichannel Hydraulic Force Control for Aircraft Structural Loading Test System

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