Wyniki wyszukiwania - BazTech

1

Holistic Low-Effort Model for Damage Tolerance Analysis in Preliminary Design

Rohdenburg Michael, Runge Fabian, Haupt Matthias, Markgraf Lennart, Horst Peter, Heimbs Sebastian

Transactions on Aerospace Research

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2022

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Nr 3 (268)

1--20

EN

The paper presents reduced order results for three different realistic scenarios with respect to the damage tolerance behaviour. The scenarios are dedicated to stiffened structures and feature the fuselage side panel, the upper fuselage panel and a lower wing panel. A wide range of parameter variations is discussed and the influence on the inspection interval is shown. Results may be used both in preliminary aircraft design and structural optimisation.

2

Initiation and tolerance of macro-damage of first ply (FBF) in a process of damaging of hybrid multi-ply structures due to reinforcement architecture

Pieniak D.

Advances in Materials Science

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2018

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Vol. 18, nr 2(56)

77--91

EN

The objective of this paper was study and analysis of damaging process of multi-ply structure applied in dentistry. The aim was to analyze and experimentally evaluate tolerance of macro-damage of first ply (FPF - first ply failure) of multi-ply composite. A studied structure of composite makes a carrying structure for dental applications e.g. adhesive bridges. Influence of reinforcement structure on the residual carrying capacity of the studied multi-ply materials has been demonstrated. It has been shown that the type of fiber and fiber ribbon architecture play a major role in strength of studied reinforcements. Structures included in the study differ by the moment of macro-damage occurrence, carrying capacity and residual stiffness.

3

Predictive Models for Transient Loads of the Vertical Stabilizer of an Aircraft developed using Canonican Correlation Analision

Dziendzikowski M., Zieliński W., Obrycki Ł., Woch M., Synaszko P., Dragan K., Leski A.

Fatigue of Aircraft Structures

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2015

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Iss. 7

41--46

EN

Knowledge about loads occurring in the structure during aircraft operation is vital from the point of view of the damage tolerance approach to aircraft design. In the best-life scenario, such information could be available from a network of sensors, e.g. strain gauges, installed in the aircraft structure to measure local stresses. However, operational loads monitoring (OLM) systems are still not widely applied. Instead, what is available is a set of flight parameters, which by the laws of inertia and aerodynamics help determine the dominant part of loads acting on a given element. This paper discusses the canonical correlation analysis (CCA) as a method for selecting the flight parameters used to predict aircraft loads. CCA allows for the identification of both different modes of stress distribution as well as flight parameters which are best suited for their prediction. The paper presents the application of this method to identify loads acting on the vertical stabilizer of an aircraft.

4

Statistical damage mechanics - constitutive relations

Rinaldi A., Krajcinovic D., Mastilovic S.

Journal of Theoretical and Applied Mechanics

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2006

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Vol. 44 nr 3

585-602

EN

The statistical damage model presented by the authors in the previous paper of this series is used to formulate analytical constitutive relations for the hardening and softening phases of two-dimensional lattices. A proper definition of the damage parameter for the softening is introduced. The results confirm that the analytical model can be used for the study of the softening phase and failure. This research offers a seminal basis for Damage Tolerance Principles technology standards of the commercial airplane industry.

PL

Statystyczny model uszkodzenia, przedstawiony przez autorów w innej pracy, zastosowano tu do sformułowania analitycznych związków konstytutywnych w zakresie wzmocnienia i osłabienia dla dwuwymiarowych modeli sieciowych. Wprowadzono odpowiednią definicję parametru uszkodzenia w zakresie osłabienia. Uzyskane wyniki potwierdzają, że wprowadzony model analityczny można stosować do badania osłabienia i zniszczenia materiałów. Praca stanowić może podstawę do ustalenia norm technicznych uszkodzenia stosowanych w przemyśle lotniczym.