Identiﬁcation of honeycomb sandwich properties by high-resolution modal analysis

Rébillat, Marc; Boutillon, Xavier

doi:10.1051/epjconf/20100641005

Cited by 2 publications

(2 citation statements)

References 10 publications

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“…Due to its excellent mechanical properties and lightweight structural characteristics, the main panel structure of many spacecraft is composed of honeycomb sandwich panels. [10][11][12][13] Generally, the mass of the honeycomb sandwich panels can account for 80-90% of the entire spacecraft panel structure. [14][15][16][17][18] Since there is no honeycomb structure unit in current general aerospace product engineering software, such as Nastran, only the real physical model and the equivalent models based on equivalence theories can be used to simulate the structure with honeycomb sandwich panels.…”

Section: Introductionmentioning

confidence: 99%

Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays

Wang

Luo

Jia

et al. 2020

Advanced Composites Letters

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Due to the difficulty of direct finite-element modeling for honeycomb sandwich panels, it is more common to apply equivalent modeling theories. It is necessary to compare their equivalent precision and then to determine the method with the best equivalent performance so as to prepare for the application in satellite solar arrays. The first 10 natural frequencies are obtained by analyzing the dynamic characteristics of sandwich panel theory model, honeycomb panel theory model, and equivalent panel theory model. The equivalent errors of different equivalent methods are obtained by comparison with the analysis results of real honeycomb panel model. Then, the sandwich panel theory and the Hoff theory with high precision are used to simulate the solar array panel. The two methods are further verified and compared by simulation and experiment. Finally, the sandwich panel theory with the highest accuracy is selected to simulate the vibration response of the solar array panel based on the above work. By comparing the frequency response analysis results with the test results, it is found that the maximum acceleration response error is within 7%, and the corresponding frequency error of the main direction is within 3%. The comparison between random analysis results and test results shows that the root mean square response errors of acceleration in three directions are within 13.7%. It is proved that the sandwich panel theory has high accuracy in the honeycomb structure. Based on the background of a specific space project, this study innovatively applies the test results to compare several typical equivalent theories of honeycomb sandwich panels so as to get a theory with the highest equivalent precision. The final conclusion has been applied to the design of related space products and proved to be feasible. This provides important reference and basis for the structural design of the satellite.

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Section: Introductionmentioning

confidence: 99%

Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays

Wang

Luo

Jia

et al. 2020

Advanced Composites Letters

View full text Add to dashboard Cite

show abstract

“…ey provide the advantages of high specific stiffness and specific strength and good heat insulation, vibration isolation, and impact resistance [3][4][5][6][7]. Honeycomb sandwich panel structures comprise 80-90% of the shell and shell structure of spacecraft [8,9].…”

Section: Introductionmentioning

confidence: 99%

Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis

Luo

Wang

et al. 2019

Shock and Vibration

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The modal analysis of a satellite sailboard finite element model is carried out to accurately investigate the response of a satellite sailboard in a complex loaded space environment through simulation. The basic excitation vibration test of the satellite sailboard is used to perform model matching and a correlation test. Appropriate design variables are selected through sensitivity analysis. Modal analysis data and vibration table excitation test response data are used to modify the finite element model. After optimization, the orthogonality of the simulated vibration mode and experimental vibration mode is good. The low-order frequency errors in the simulation model are less than 5%, the high-order errors are less than 10%, and the modal confidence MAC values are above 0.8. The modal frequency and mode shape are closer to the experimental modal frequency and mode shape, respectively. The simulation and test acceleration response of the modified finite element model of a honeycomb panel are compared under the two conditions of sine sweep and random vibration. The acceleration response curves of reference points are consistent, and amplitude and frequency errors are within acceptable limits. The model updating effect is evident, which provides good reference for research on satellites and other aerospace products.

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Identiﬁcation of honeycomb sandwich properties by high-resolution modal analysis

Cited by 2 publications

References 10 publications

Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays

Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays

Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis

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