Electrically Driven And Controlled Landing Gear For UAV Up To 100kg Of Take Off Mass

Skorupka, Zbigniew; Kowalski, Wojciech; Kajka, R.

doi:10.7148/2010-0117-0121

Cited by 2 publications

(1 citation statement)

References 1 publication

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“…The torque-speed envelope profile is determined by specifying the maximum torque and power [35]; these values have been estimated from similar systems [36]. The motor is driven by an ideal voltage source that maintains constant voltage across its output terminals, independent of the current flowing through the source, simulating the batteries used in a real vehicle.…”

Section: The Steering Systemmentioning

confidence: 99%

Preliminary Nose Landing Gear Digital Twin for Damage Detection

Pinello,

Hassan,

Giglio

et al. 2024

Aerospace

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An increase in aircraft availability and readiness is one of the most desired characteristics of aircraft fleets. Unforeseen failures cause additional expenses and are particularly critical when thinking about combat jets and Unmanned Aerial Vehicles (UAVs). For instance, these systems are used under extreme conditions, and there can be situations where standard maintenance procedures are impractical or unfeasible. Thus, it is important to develop a Health and Usage Monitoring System (HUMS) that relies on diagnostic and prognostic algorithms to minimise maintenance downtime, improve safety and availability, and reduce maintenance costs. In particular, within the realm of aircraft structures, landing gear emerges as one of the most intricate systems, comprising several elements, such as actuators, shock absorbers, and structural components. Therefore, this work aims to develop a preliminary digital twin of a nose landing gear and implement diagnostic algorithms within the framework of the Health and Usage Monitoring System (HUMS). In this context, a digital twin can be used to build a database of signals acquired under healthy and faulty conditions on which damage detection algorithms can be implemented and tested. In particular, two algorithms have been implemented: the first is based on the Root-Mean-Square Error (RMSE), while the second relies on the Mahalanobis distance (MD). The algorithms were tested for three nose landing gear subsystems, namely, the steering system, the retraction/extraction system, and the oleo-pneumatic shock absorber. A comparison is made between the two algorithms using the ROC curve and accuracy, assuming equal weight for missed detections and false alarms. The algorithm that uses the Mahalanobis distance demonstrated superior performance, with a lower false alarm rate and higher accuracy compared to the other algorithm.

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Section: The Steering Systemmentioning

confidence: 99%

Preliminary Nose Landing Gear Digital Twin for Damage Detection

Pinello,

Hassan,

Giglio

et al. 2024

Aerospace

View full text Add to dashboard Cite

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A new concept for UAV landing gear shock vibration control using pre-straining spring momentum exchange impact damper

Son

Bur

Rusli

2016

Journal of Vibration and Control

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This study proposes a new method for reducing the shock vibration response of an Unmanned Aerial Vehicle (UAV) during the landing process by means of the momentum exchange principle (MEID). The performance of the impact damper is improved by adding a pre-straining spring to the damper system. This research discusses the theoretical application of the damper to the UAV landing gear system. The UAV dynamics is first modeled as a simple lumped mass translational vibration system. Then we analyze a more complex two-dimensional model of UAV dynamics. This model consists of the main wheel, nose wheel and main body. Three cases of UAV landing gear mechanisms: without damper, with passive MEID (PMEID) and with pre-straining spring MEID (PSMEID) are simulated. The damper performance is evaluated from the maximum acceleration and force transmission to the main body. The energy balance calculation is conducted to investigate the performance of PSMEID. The simulation results show that the proposed PSMEID method is the most effective method for reducing the maximum acceleration and force transmission of UAV during impact landing.

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Electrically Driven And Controlled Landing Gear For UAV Up To 100kg Of Take Off Mass

Cited by 2 publications

References 1 publication

Preliminary Nose Landing Gear Digital Twin for Damage Detection

Preliminary Nose Landing Gear Digital Twin for Damage Detection

A new concept for UAV landing gear shock vibration control using pre-straining spring momentum exchange impact damper

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