Homogenization of Integrated Thermal Protection System with Rigid Insulation Bars

Ravishankar, Bharani; Sankar, Bhavani V.; Haftka, Raphael T.

doi:10.2514/6.2010-2687

Cited by 11 publications

(3 citation statements)

References 9 publications

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“…At present, the spacecraft's health management system is mainly aimed at the two modules of heat protection and engine, and has achieved very good results. In terms of thermal protection, the bending and buckling of Integrated Thermal Protection System (ITPS) are usually considered [3]. The fatigue damage caused by temperature gradient is mainly considered for the possible failure of engine in operation.…”

Section: Introductionmentioning

confidence: 99%

Strength Check of Aircraft Parts Based on Multi-GPU Clusters for Fast Calculation of Sparse Linear Equations

Zhang

Hu²

2020

IEEE Access

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In order to improve the cost-effectiveness ratio, the next-generation vehicle needs to meet the requirements of reuse, while adopting a lighter structural weight, so it is necessary to realize the strength calculation and condition monitoring of key components in the digital twin. Most of the current monitoring methods are based on the characteristics of various data acquisition systems, but they need the support of a large number of flight data. The disadvantages of the above strategy can be avoided by reducing the structure of aircraft components to a finite element model and quickly checking the key components in the health management system. In order to solve the problem of fast calculation of the finite element model of the key components of the aircraft, a parallel algorithm and framework of large-scale sparse matrix preprocessing conjugate gradient method based on CUDA(Compute Unified Device Architecture) technology is proposed in the multi GPU(Graphics Processing Unit) workstation cluster environment. Once the sparse matrix is too large to be processed in a single workstation, this paper discusses how to realize the optimized data segmentation in the distributed multi-GPU computing environment. For the problem of iterative solution of matrix preprocessing, two preprocessing strategies of matrix bandwidth reduction parallelization and incomplete Cholesky decomposition are proposed, and asynchronous task concurrency and load balancing strategies are designed on the architecture. The calculation of some examples in the standard sparse matrix database shows that the algorithm and architecture proposed in this paper have the ability to solve large-scale sparse matrix quickly and efficiently, and can complete the fast strength verification of vehicle components.

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Section: Introductionmentioning

confidence: 99%

Strength Check of Aircraft Parts Based on Multi-GPU Clusters for Fast Calculation of Sparse Linear Equations

Zhang

Hu²

2020

IEEE Access

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“…Bourada 11 and Tounsi et al 12 studied the instability of a honeycomb core with a uniform wall thickness under uni-and bidirectional inplane compression and out-of-plane compression. Using experimental studies and numerical simulations, A. Boudjemai 31 and Amri et al 32 studied the macroscopic deformation and plastic instability of a honeycomb structure with uniform wall thicknesses under unidirectional in-plane compression.…”

Section: Introductionmentioning

confidence: 99%

The mechanical behaviour of new long-span hollow-core roofs based on aluminum alloy honeycomb panels

Zhao¹,

Ma²,

Du³

2019

Mater. Tehnol.

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This article proposes a new type of spatial structure that is based on the principle of an aviation structure skin force bearing. The structure consists of honeycomb panels and specialized connecting pieces to spatially combine the honeycomb panels and form a novel skeleton-free hollow-core roof system (referred to as a "honeycomb panel structural system" (HPSS)). To evaluate the stitching results of the new structure, its connection performance, failure mechanism and limiting load were examined, and the full-scale samples that were designed and manufactured from two sets of HPSS were employed to conduct the experimental research. The results indicated that the new structure has a high spatial stiffness and loading capacity. The failure mode of the two test specimens comprises the shear damage of the connector and the buckling failure of the honeycomb panel. The existing rectangular sandwiched honeycomb panel buckling theory cannot correctly reflect the plastic deformation or failure of the sandwiched material, this paper obtained the analysis method for the honeycomb panel buckling characteristic value that is consistent with practical conditions. Using different simulation methods, the comparative analysis results revealed that the finite-element coupling method proposed in this paper can adequately simulate the actual operating state of the connector between two honeycomb panels. This method is feasible, highly efficient, and provides a theoretical basis for future revision of the design rules for this new type of spatial structure.

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“…Bourada M, Tounsi A et al [11,12] studied the instability of a honeycomb core with a uniform wall thickness under uni-and bidirectional in-plane compression and out-of-plane compression. Using experimental studies and numerical simulations, A. Boudjemai, R. Amri et al [25,26] studied the macroscopic deformation and plastic instability of a honeycomb structure with uniform wall thicknesses under unidirectional in-plane compression.…”

Section: Introductionmentioning

confidence: 99%

The Stability of New Single-Layer Combined Lattice Shell Based on Aluminum Alloy Honeycomb Panels

Zhao

2017

Applied Sciences

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This article proposes a new type of single-layer combined lattice shell (NSCLS); which is based on aluminum alloy honeycomb panels. Six models with initial geometric defect were designed and precision made using numerical control equipment. The stability of these models was tested. The results showed that the stable bearing capacity of NSCLS was approximately 16% higher than that of a lattice shell with the same span without a reinforcing plate. At the same time; the properties of the NSCLS were sensitive to defects. When defects were present; its stable bearing capacity was decreased by 12.3% when compared with the defect-free model. The model with random defects following a truncated Gaussian distribution could be used to simulate the distribution of defects in the NSCLS. The average difference between the results of the nonlinear analysis and the experimental results was 5.7%. By calculating and analyzing nearly 20,000 NSCLS; the suggested values of initial geometric defect were presented. The results of this paper could provide a theoretical basis for making and revising the design codes for this new combined lattice shell structure.

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Homogenization of Integrated Thermal Protection System with Rigid Insulation Bars

Cited by 11 publications

References 9 publications

Strength Check of Aircraft Parts Based on Multi-GPU Clusters for Fast Calculation of Sparse Linear Equations

Strength Check of Aircraft Parts Based on Multi-GPU Clusters for Fast Calculation of Sparse Linear Equations

The mechanical behaviour of new long-span hollow-core roofs based on aluminum alloy honeycomb panels

The Stability of New Single-Layer Combined Lattice Shell Based on Aluminum Alloy Honeycomb Panels

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