Experimental Validation of a Computational Hybrid Methodology to Estimate Fuselage Damage Due to Harsh Landing

Sbarufatti, Claudio; Vallone, Giorgio; Giglio, Marco; Stefaniuk, M.; Leski, Andrzej; Zieliński, Wojciech

doi:10.4050/jahs.61.042008

Cited by 4 publications

(2 citation statements)

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“…That work aimed to investigate the interaction between the landing devices and the terrain under realistic conditions, and analyzing the effects of realistic ground loads on the rotor components. Other works specifically focused on the rotorcraft harsh landing proposed interesting landing simulation techniques [33,34], introducing on-board monitoring techniques (e.g., health monitoring systems) able to assess the structural integrity of the helicopter fuselage [33][34][35][36][37]. In [38,39] a tool for aircraft hard landing detection is suggested, being able to reveal landing gear overloads.…”

Section: State Of the Artmentioning

confidence: 99%

“…Further experimental measurements consisted of optical scanning of the skin surface in some specific areas, performed after each drop event. Structural deformation analysis was achieved by comparing the same scanned surface morphology before and after the landing event, to detect eventual permanent (i.e., plastic) deformations [34,36].…”

Section: Experimental Activitymentioning

confidence: 99%

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On the Evaluation of a Coupled Sequential Approach for Rotorcraft Landing Simulation

Cristiani

Colombo

Zieliński

et al. 2020

Sensors

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Maximum loads acting on aircraft structures generally arise when the aircraft is undergoing some form of acceleration, such as during landing. Landing, especially when considering rotorcrafts, is thus crucial in determining the operational load spectrum, and accurate predictions on the actual health/load level of the rotorcraft structure cannot be achieved unless a database comprising the structural response in various landing conditions is available. An effective means to create a structural response database relies on the modeling and simulation of the items and phenomena of concern. The structural response to rotorcraft landing is an underrated topic in the open scientific literature, and tools for the landing event simulation are lacking. In the present work, a coupled sequential simulation strategy is proposed and experimentally verified. This approach divides the complex landing problem into two separate domains, namely a dynamic domain, which is ruled by a multibody model, and a structural domain, which relies on a finite element model (FEM). The dynamic analysis is performed first, calculating a set of intermediate parameters that are provided as input to the subsequent structural analysis. Two approaches are compared, using displacements and forces at specific airframe locations, respectively, as the link between the dynamic and structural domains.

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