Damage tolerance based design optimisation of a fuel flow vent hole in an aircraft structure

2008 ◽  
Vol 38 (3) ◽  
pp. 245-265 ◽  
Author(s):  
R. Das ◽  
R. Jones
Keyword(s):  
Damage Tolerance ◽  
Aircraft Structure ◽  
Design Optimisation ◽  
Fuel Flow

scholarly journals Corrosion Monitoring of Aircraft Based on the Corrosion Prognostic Health Management (CPHM) System

2020 ◽  
Vol 50 (4) ◽  
pp. 205-216
Author(s):  
Patryk Ciężak ◽  
Adam Rdzanek
Keyword(s):  
Damage Tolerance ◽  
Health Management ◽  
Actual State ◽  
Corrosion Monitoring ◽  
Field Site ◽  
Aircraft Structure ◽  
Corrosion Detection ◽  
Preliminary Results ◽  
Forecasting Methods ◽  
Prognostic Health Management

AbstractThe article presents methods to monitor the actual state of aircraft’s airframe, in particular, the onset of corrosion. The greatest emphasis is put on the “Corrosion Prognostic Health Management” CPHM system. Authors discuss corrosion detection using NDT methods as well as the possibilities of forecasting methods for estimating the onset of corrosion basing on the data gathered by means corrosion sensors. Based on the results of the previous research and analyses, authors focus on monitoring the internal microclimate and the factors causing corrosion in the aspect of damage tolerance operation of the aircraft. The results of the preliminary studies giving credibility to the concepts of predicting corrosion onset in the aircraft structure are presented. Preliminary results of tests carried out in supervised flights are also presented. The final part of the article presents the concept of modernizing the corrosion field site in order to use it in hermetic and non-hermetic tests of aircraft spaces.

Investigation on Damage Tolerance of Thick Laminate Composite Structure

2015 ◽  
Vol 665 ◽  
pp. 149-152
Author(s):  
Hyun Bum Park
Keyword(s):  
Standardized Test ◽  
Damage Tolerance ◽  
Impact Damage ◽  
Specimen Thickness ◽  
Aircraft Structure ◽  
Functional Capability ◽  
Damage Level ◽  
Typical Specimen ◽  
Standard Design ◽  
Laminate Composite Structure

This study is to investigate the compressive strength of the carbon/epoxy thick laminate after damage. Through damage tolerance of thick laminate is not standardized test because specimens exceed typical specimen thickness described in the ASTM standard, design allowable of thick laminate shall be determined by the experiment to address design criteria of the structure and incorporate functional capability with damage level. In this study, it is performed the research on damage tolerance of thick laminate adopting aircraft structure. The damage tolerance of thick laminates such as no damage and impact damage is evaluated under compression loading.

Residual Strength Optimisation of a Vent Hole in an Aircraft Component Using a Heuristic Method

2011 ◽  
Vol 275 ◽  
pp. 105-108
Author(s):  
Raj Das ◽  
Rhys Jones
Keyword(s):  
Residual Strength ◽  
Damage Tolerance ◽  
Heuristic Method ◽  
Initial Crack ◽  
Shape Optimisation ◽  
Initial Shape ◽  
Fuel Flow ◽  
Component Design ◽  
Aircraft Component ◽  
Tolerance Optimisation

The paper presents application of damage tolerance optimisation principles to the design of industrial components. It is illustrated via design optimisation of a Fuel Flow Vent Hole (FFVH) located in the Wing Pivot Fitting (WPF) of an F-111 aircraft. The aim is to determine the shape of the cutout that will maximise its residual strength under the operating loading conditions. Damage tolerance shape optimisation is performed using a heuristic optimisation method known as the ‘Biological algorithm’. The maximum stress intensity factor (SIF) for all of the cracks around the boundary of the optimal cutout is found to be significantly lower compared to that of the initial shape. This shows that an improved residual (fracture) strength is achieved for the optimal designs. The variability in SIF around the cutout boundary is reduced, thereby making the shape more evenly fracture critical. The shapes of the residual strength optimal vent holes are found to depend on the initial crack sizes. It is also shown that a damage tolerance optimisation additionally produces a lighter WPF component design, which is highly desirable for aerospace industries.

Study on the Damage Tolerance of a Stiffened Panel with a Skin Pad

2008 ◽  
Vol 33-37 ◽  
pp. 297-300
Author(s):  
Yi Li ◽  
Sheng Nan Wang
Keyword(s):  
Crack Propagation ◽  
Static Analysis ◽  
Damage Tolerance ◽  
Fortran Program ◽  
Structure Design ◽  
Stiffened Panel ◽  
Manufacturing Cost ◽  
Aircraft Structure ◽  
Propagation Experiment ◽  
Crack Propagation Experiment

During the development of an aircraft structure design, designers draw out a skin-stringer panel with a skin pad on the basis of a conventional skin-stringer panel(skin is directly connected with stringer by rivets or there was a sheet betweeen skin and stringers) to reduce the manufacturing cost. In this paper, we calculated the SIF of three kinds of skin-stringer panels by FE. And then, we analyze the damage tolerance of these structures by fortran program. Especially we carried out a crack propagation experiment of a skin-stringer panel with a skin pad and compared it with the results of a static analysis. Finally we researched the influence of the thickness of a skin pad on the damage tolerance. According to the researches above we concluded the advantages of the skin-stringer panel with a skin pad on the damage tolerance, and presented some suggestions about the thickness of a skin pad.

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

2015 ◽  
Vol 2015 (7) ◽  
pp. 41-46
Author(s):  
Michał Dziendzikowski ◽  
Wojciech Zieliński ◽  
Łukasz Obrycki ◽  
Marta Woch ◽  
Piotr Synaszko ◽  
...  
Keyword(s):  
Damage Tolerance ◽  
Aircraft Design ◽  
Point Of View ◽  
Strain Gauges ◽  
Aircraft Structure ◽  
Local Stresses ◽  
Tolerance Approach ◽  
Flight Parameters ◽  
Aircraft Loads ◽  
Dominant Part

Abstract 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.

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