Structural design and test capability of a CFRP aileron

Romano, Fulvio; Fiori, J. J.; Mercurio, Umberto

doi:10.1016/j.compstruct.2008.04.010

Cited by 13 publications

(9 citation statements)

References 3 publications

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“…The following equations were used to study the kinematic model for the second iteration: Rt = r + s (Eq. [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19] With the above relationships and the use of MATLAB, a graphical approach was used to iterate to a final model. By setting a constant y-ratio and iterating through various x-ratios, an improved R-R-P-R design was developed.…”

Section: Figure 3-10: Cant Angle Vs Slider Displacement/load Anglementioning

confidence: 99%

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Design and Analysis of a Dynamic Loading System for a Morphing Winglet

Buchkazanian¹

2021

Preprint

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The following thesis paper investigates the possible methods to perform a dynamic load test on a morphing winglet. A morphing winglet design capable of deflecting in the cant direction was developed by a joint partnership between Ryerson University and Bombardier Aerospace. In order to validate the model and complete a proof of concept, a loading fixture was required to test the structural integrity of the winglet under a defined load. Upon completion of an enumeration study of planar four-bar linkages, a passive R-P-R-P mechanism was designed to apply a constant perpendicular load throughout the cant motion. A design of the half size loading fixture was developed, optimized and manufactured to integrate with an existing cant module. The dynamic loading model was validated by producing a positive correlation between the theoretical analysis and the experimental results, leading to a successful proof of concept for a full scale test.

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Section: Figure 3-10: Cant Angle Vs Slider Displacement/load Anglementioning

confidence: 99%

“…3- 21) and (Eq. [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22], the actuator's stroke requirements to achieve a 10°− 80° motion becomes a function of the distance between R1 and P4. By using the provided moment arm of 20-inches, the plots in Figure 3-23 were obtained.…”

Section: Figure 3-21: R-p-r-p Kinematic Modelmentioning

confidence: 99%

Design and Analysis of a Dynamic Loading System for a Morphing Winglet

Buchkazanian¹

2021

Preprint

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“…Romano et al [5] carried out research activities on the design of a new CFRP aileron, considering as a baseline reference an aluminium aileron installed on the P180 AVANTI aircraft. Composite laminates used for such structure were manufactured by using the Resin Transfer Moulding (RTM) process.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigation on the Structural Behaviour of a Horizontal Stabilizer under Critical Aerodynamic Loading Conditions

Sepe

Citarella

Luca

et al. 2017

Advances in Materials Science and Engineering

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The aim of the proposed research activity is to investigate the mechanical behaviour of a part of aerospace horizontal stabilizer, made of composite materials and undergoing static loads. The prototype design and manufacturing phases have been carried out in the framework of this research activity. The structural components of such stabilizer are made of composite sandwich panels (HTA 5131/RTM 6) with honeycomb core (HRH-10-1/8-4.0); the sandwich skins have been made by means of Resin Transfer Moulding (RTM) process. In order to assess the mechanical strength of this stabilizer, experimental tests have been performed. In particular, the most critical inflight recorded aerodynamic load has been experimentally reproduced and applied on the stabilizer. A numerical model, based on the Finite Element Method (FEM) and aimed at reducing the experimental effort, has been preliminarily developed to calibrate amplitude, direction, and distribution of an equivalent and simpler load vector to be used in the experimental test. The FEM analysis, performed by using NASTRAN code, has allowed modelling the skins of the composite sandwich plates by definition of material properties and stack orientation of each lamina, while the honeycomb core has been modelled by using an equivalent orthotropic plate. Numerical and experimental results have been compared and a good agreement has been achieved.

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“…Due to their high strength and low density, these composites were initially developed for weight-critical applications. 1,2 With the advances in manufacturing techniques and the resulted decrease in the production cost, they are now widely used not only on aircrafts, 3,4 but also for automobiles, 5,6 sports equipment, 7,8 etc.…”

Section: Introductionmentioning

confidence: 99%

Initiation of structural defects in carbon fiber reinforced polymer composites under hygrothermal environments

Zhong

Joshi

2015

Journal of Composite Materials

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Exposure to hygrothermal environments affects mechanical properties of laminated composites through two principle mechanisms, namely, moisture absorption and the structural deterioration due to it. Previous studies have indicated that moisture plays a positive role in carbon fiber reinforced polymer composites by alleviating their damage under impact. In this study, carbon fiber reinforced polymer composites were exposed to long-term hygrothermal ageing to investigate the possibility of the initiation of structural defects due to it and their influences on the various behaviors of the laminated composites. A major type of observable structural defects was identified and the related initiation mechanism was proposed. It was found for the first time that the structural defects formed during hygrothermal ageing in turn changed the moisture uptake profile of the laminated composites. The effects of structural defects on the impact resistance of carbon fiber reinforced polymer composites were exclusively evaluated after removing the absorbed moisture. Tensile testing on vacuum-oven-dried laminates was conducted to assist the understanding of the mechanical strength of the carbon fiber reinforced polymer composites exposed to the hygrothermal environments.

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Structural design and test capability of a CFRP aileron

Cited by 13 publications

References 3 publications

Design and Analysis of a Dynamic Loading System for a Morphing Winglet

Design and Analysis of a Dynamic Loading System for a Morphing Winglet

Numerical and Experimental Investigation on the Structural Behaviour of a Horizontal Stabilizer under Critical Aerodynamic Loading Conditions

Initiation of structural defects in carbon fiber reinforced polymer composites under hygrothermal environments

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