Thermo-structural design of a Ceramic Matrix Composite wing leading edge for a re-entry vehicle

Ferraiuolo, Michele; Scigliano, Roberto; Riccio, Aniello; Bottone, Emanuele; Rennella, Marco

doi:10.1016/j.compstruct.2018.09.024

Cited by 24 publications

(12 citation statements)

References 20 publications

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“…The aerodynamic heating maximum value encountered during the re-entry mission for the stagnation point is 400 kW/m 2 and is reached after 1200 s. The entire re-entry trajectory lasts 3700 s [1].…”

Section: Thermal and Structural Boundary Conditionsmentioning

confidence: 97%

“…It should be underlined that the aim of this paper is not the redesign of the component, but rather to demonstrate the advantages of the adoption of sub-modeling techniques to accurately and effectively predict the thermo-mechanical behavior of complex ceramic matrix composite components. As a matter of fact, the presented sub-modeling approach could be easily employed in the future to redesign and/or optimize the skin of the WLE presented in [1]. According to Figure 4, the size of the local model has been varied, in the frame of a preliminary trade-off study, to investigate the influence of the distance of the boundaries of the local model from the area of interest, on the accuracy of results.…”

Section: Sub-modelingmentioning

confidence: 99%

“…The present work reports the follow-on research activity of a previous research work on the thermo-structural design of a ceramic matrix composite wing leading edge (WLE) of a re-entry vehicle [1]. Actually, in [1], the main aim was to minimize the thermal stresses occurring at the interfaces between the external hot structure and the internal cold structure by introducing new materials and new design solutions, in order to improve the design solutions described in [2] where ultra high temperature ceramics (UHTC) were employed. The results obtained in [1], in terms of weight savings and structural reliability, were considered very promising even if a simplified numerical model, based on an equivalent orthotropic material model, was adopted to simulate the skin of the WLE.…”

Section: Introductionmentioning

confidence: 99%

“…Actually, in [1], the main aim was to minimize the thermal stresses occurring at the interfaces between the external hot structure and the internal cold structure by introducing new materials and new design solutions, in order to improve the design solutions described in [2] where ultra high temperature ceramics (UHTC) were employed. The results obtained in [1], in terms of weight savings and structural reliability, were considered very promising even if a simplified numerical model, based on an equivalent orthotropic material model, was adopted to simulate the skin of the WLE. Actually, with this material model, no information on the thermomechanical behaviour of each ply and its potential failure was available, leading to a very conservative design not fully exploiting the potential benefits of ceramic matrix composites.…”

Section: Introductionmentioning

confidence: 99%

“…In the present paper, the authors aim to demonstrate that sub-modeling techniques can represent a very valuable solution for the design of a complex component subjected to very high thermo-mechanical loads, such as the ceramic matrix composite wing leading edge of a re-entry vehicle. Figures 1 and 2 show the configuration resulting from the design process described in [1] that will be used at test bench in the present paper. Indeed, for this specific component, the need for detailed thermo-mechanical analyses is accompanied by the need for a detailed representation, at layer level, of the complex structure of ceramic matrix composite materials, leading to unfeasible computational costs.…”

Section: Introductionmentioning

confidence: 99%

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Investigating the Thermo-Mechanical Behavior of a Ceramic Matrix Composite Wing Leading Edge by Sub-Modeling Based Numerical Analyses

et al. 2020

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The thermo-structural design of the wing leading edge of hypersonic vehicles is a very challenging task as high gradients in thermal field, and hence high thermal stresses, are expected. Indeed, when employing passive hot structures based thermal protection systems, very high temperatures (e.g., 1400 °C) are expected on the external surface of the wing leading edge, while the internal structural components are required to not exceed a few hundred degrees Celsius (e.g., 400 °C) at the interface with the internal cold structure. Hence, ceramic matrix composites (CMC) are usually adopted for the manufacturing of the external surface of the wing leading edge since they are characterized by good mechanical properties at very high temperatures (up to 1900 °C) together with an excellent thermal shock resistance. Furthermore, the orthotropic behavior of these materials together with the possibility to tailor their lamination sequence to minimize the heat transferred to internal components, make them very attractive for hot structure based thermal protection systems applications. However, the numerical predictions of the thermo-mechanical behavior of such materials, taking into account the influence of each ply (whose thickness generally ranges between 0.2 and 0.3 mm), can be very expensive from a computational point of view. To overcome this limitation, usually, sub-models are adopted, able to focus on specific and critical areas of the structure where very detailed thermo-mechanical analyses can be performed without significantly affecting the computational efficiency of the global model. In the present work, sub-modeling numerical approaches have been adopted for the analysis of the thermo-mechanical behavior of a ceramic matrix composite wing leading edge of a hypersonic vehicle. The main aim is to investigate the feasibility, in terms of computational efficiency and accuracy of results, in using sub-models for dimensioning complex ceramic matrix components. Hence, a comprehensive study on the size of sub-models and on the choice of their boundaries has been carried out in order to assess the advantages and the limitations in approximating the thermo-mechanical behavior of the investigated global ceramic matrix composite component.

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Section: Thermal and Structural Boundary Conditionsmentioning

confidence: 97%

Section: Sub-modelingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Investigating the Thermo-Mechanical Behavior of a Ceramic Matrix Composite Wing Leading Edge by Sub-Modeling Based Numerical Analyses

et al. 2020

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Characterization of Ultra‐High Temperature and Polymorphic Ceramics

Radhi

Behdinan

2021

Advanced Multifunctional Lightweight Aerostructures; Design, Development, and Implementation

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Processing of fiber‐reinforced ultra‐high temperature ceramic composites: A review

Rueschhoff

Carney

Apostolov

et al. 2019

Int J Ceramic Engine & Sci

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Ultra-high temperature ceramics (UHTCs) have emerged as promising materials for high-temperature aerospace applications due to their high melting temperature and superior ablation performance. Even still, they have yet to reach their full potential due to the catastrophic brittle failure that typically accompanies the intrinsic low fracture toughness of ceramic materials. Therefore, the emerging field of UHTC ceramic matrix composites (UHTCMCs) offers the toughness benefits of a composite with the high temperature stability of UHTCs. Here, we outline work in the last decade on the processing of UHTCs with a reinforcing fiber phase for enhanced fracture toughness. Included are fibers of both carbon and silicon carbide composition in both continuous and chopped fiber lengths. Particular emphasis is given to emerging research from the last few years to highlight novel developments. K E Y W O R D Sceramic matrix composites, ceramic processing, ultra-high temperature ceramics How to cite this article: Rueschhoff LM, Carney CM, Apostolov ZD, Cinibulk MK. Processing of fiber-reinforced ultra-high temperature ceramic composites: A review.

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Thermo-structural design of a Ceramic Matrix Composite wing leading edge for a re-entry vehicle

Cited by 24 publications

References 20 publications

Investigating the Thermo-Mechanical Behavior of a Ceramic Matrix Composite Wing Leading Edge by Sub-Modeling Based Numerical Analyses

Investigating the Thermo-Mechanical Behavior of a Ceramic Matrix Composite Wing Leading Edge by Sub-Modeling Based Numerical Analyses

Characterization of Ultra‐High Temperature and Polymorphic Ceramics

Processing of fiber‐reinforced ultra‐high temperature ceramic composites: A review

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