Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis

Luo, Haitao; Wang, Wei; Fu, Jia; Jiao, Lichuang

doi:10.1155/2019/4547632

Cited by 9 publications

(7 citation statements)

References 28 publications

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“…Luo et al performed FEM model matching of the satellite sailboard based on sensitivity analysis. e low-order frequency errors in the simulation model were less than 5%, and the high-order errors were less than 10% [17]. For the solar array of multiple plates, the parameter number is large, while the accuracy of the FEM model is insufficient.…”

Section: Introductionmentioning

confidence: 91%

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Encapsulation Based Method for Natural Frequency Identification of Deployable Solar Arrays with Multiple Plates

Zhao

Chen

et al. 2021

Shock and Vibration

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The ground modal test is an important approach to the natural frequency of solar arrays to support the attitude control of spacecraft. However, for the batch production of small satellites, the accuracy and efficiency of traditional ground modal testing methods are limited. This shortcoming restricts the development of satellite constellations. Based on the encapsulation method widely used in the computer field, this paper proposed a natural frequency identification method of deployable solar arrays with multiple plates. This method is of high accuracy and efficiency that meets the demand of attitude control and makes sense to accelerate the batch production of small satellites. First, a suspended modal test system with gravity compensation function is designed. Second, the mathematical model of the test system is established. Abstracting parts of the parameters of the test object into an encapsulated entity, the mathematical model is simplified by equivalent variables. Thus, the direct mapping relationship between the ground test result and the true natural frequency is proposed. Finally, to verify the identification accuracy, finite element analysis (FEA) and the ground modal test of a two-folder solar array simulant are carried out. The results show that the relative error of the first-order natural frequency after correction and the theoretical value is less than 3%. Meanwhile, the identification accuracy of the ground modal test is improved by more than 50%. This method improves the availability of ground test results and reduces the calculation amount, so that it is convenient for engineering applications.

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Section: Introductionmentioning

confidence: 91%

“…erefore, it is necessary to combine the second type of method, that is, the correction of the systematic errors. Usually, a finite element model for model updating or a theoretical model for error estimation is established [14,15]. e accurate parameters in models are obtained by a series of tests.…”

Section: Introductionmentioning

confidence: 99%

Encapsulation Based Method for Natural Frequency Identification of Deployable Solar Arrays with Multiple Plates

Zhao

Chen

et al. 2021

Shock and Vibration

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“…They assessed that updated FEM's were efficient enough to analyze the dynamic characteristics of the honeycomb sandwich plate. Recently, Luo et al 22 introduced the FEM updating of a satellite honeycomb sandwich sailboard. They selected appropriate design variables based upon sensitivity analysis results.…”

Section: Introductionmentioning

confidence: 99%

Finite element model updating of a satellite honeycomb sandwich plate in structural dynamics

Aborehab

Kamel

Nemnem

et al. 2021

International Journal of Space Structures

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The honeycomb sandwich structures have a crucial participation in aerospace industry, especially in the design of satellite structures due to their exceptional mechanical properties. The equivalent finite element modeling of such structures is initially presented through the implementation of modal analysis via the three-layered sandwich theory. Subsequently, the computational results are validated by carrying out an experimental modal testing. In addition, sensitivity analysis based upon design of experiments and parameters correlation, is executed for the sake of selecting the most appropriate design parameters for the optimization problem. Finally, finite element model updating of a honeycomb sandwich plate is thoroughly introduced using three optimization algorithms including genetic algorithms, adaptive-multiple optimization, and response surface method. A good agreement between the previously-mentioned optimization algorithms is obtained. Meanwhile, response surface method and its related design of experiments tool succeed in avoiding such time-consuming process and reduce the involved computational expense with an acceptable accuracy.

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“…Since the honeycomb core sandwich structures have been widely used in the aerospace industry, especially in the satellite structure, some studies have focused on the vibration of the satellite structure by applying the FE method. [21][22][23][24][25][26][27][28][29][30] For example, Bai et al 22 analyzed the theory of normal modes of satellite with honeycomb sandwich plate structure using the commercial finite element PATRAN/NASTRAN software, where they performed the modal analysis of the satellite according to the equivalent model. They found that the FE method is an applicable modal analysis.…”

Section: Introductionmentioning

confidence: 99%

“…Hao et al 24 compared the three sandwich, equivalent-plate, and honeycomb-plate theories, to identify the equivalent parameters of the honeycomb sandwich plates, found that the honeycomb-plate theory is the most appropriate in simplifying the spacecraft structure. Luo et al 27 carried out the modal analysis of a satellite sailboard in a complex loaded space environment through simulation. In order to validate the results of the finite element model, they used the basic excitation vibration test of the satellite sailboard.…”

Section: Introductionmentioning

confidence: 99%

Influence of geometric parameters on free vibration behavior of an aluminum honeycomb core sandwich beam using experimentally validated finite element models

Pourriahi

Heidari-Rarani

Isfahani

2021

Jnl of Sandwich Structures & Materials

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The hexagonal honeycomb core sandwich panels used in the satellite structure are subjected to severe vibration during launch. Therefore, the amounts of natural frequencies of these panels are of great importance for design engineers. Three-dimensional finite element modeling of the core considering all geometric parameters (i.e., a high-fidelity model) to achieve accurate results is not cost-effective. The honeycomb core is traditionally equivalent to a homogenized continuum core (i.e., a low-fidelity model) using simple analytical relations with ignoring the adhesive layer at the double cell-walls and radius of inclined cell-wall curvature. In this study, analytical formulations are first presented for the prediction of the equivalent elastic properties of a hexagonal aluminum honeycomb with considering all geometric parameters including adhesive layer thickness, cell-wall thickness, inclined cell-wall length, radius of inclined cell-wall curvature at the intersection, internal cell-wall angle, and honeycomb height. Then, two aluminum honeycomb core sandwich beams with free-free boundary conditions are modeled and analyzed in Abaqus finite element software, one with 3D high-fidelity core and the other with 3D low-fidelity core. In order to validate the results of the equivalent model, the modal analysis test was performed and the experimental natural frequencies were compared. The obtained results show a good agreement between the 3D low-fidelity and high-fidelity finite element models and experimental results. In addition, the influence of the above-mentioned geometric parameters has been investigated on the natural frequencies of a sandwich beam. [Formula: see text]

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Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis

Cited by 9 publications

References 28 publications

Encapsulation Based Method for Natural Frequency Identification of Deployable Solar Arrays with Multiple Plates

Encapsulation Based Method for Natural Frequency Identification of Deployable Solar Arrays with Multiple Plates

Finite element model updating of a satellite honeycomb sandwich plate in structural dynamics

Influence of geometric parameters on free vibration behavior of an aluminum honeycomb core sandwich beam using experimentally validated finite element models

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