Natural frequency optimization of braided bistable carbon/epoxy tubes: Analysis of braid angles and stacking sequences

Wu, Chenchen; Viquerat, Andrew

doi:10.1016/j.compstruct.2016.09.075

Cited by 29 publications

(19 citation statements)

References 31 publications

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“…An FE approach was used for the vibration modal analysis of deployed BRC booms in a number of previous papers [23,24,7,21] to capture the lowest frequency vibration mode, which tends to involve a simple up-down "cantilever" motion [25] in which the boom tip locus lies only within the Y -Z (see Fig. 4) plane.…”

Section: Finite Element Model Formulationmentioning

confidence: 99%

“…A three dimensional shell model was created in ABAQUS [22] to compute the vibration characteristics of fixed-free single booms by using a linear perturbation approach [21]. Classical laminate theory (CLT) [26] was employed to capture the mechanical properties of the booms.…”

Section: Single Boom Modelmentioning

confidence: 99%

“…Classical laminate theory (CLT) [26] was employed to capture the mechanical properties of the booms. An approximate global shell element (S4R) size of 0.005 m 2 and ten elements per wavelength around the circumference (assuming a single wavelength is determined by the circumference of the boom for the first mode [21]) were used to mesh the model.…”

Section: Single Boom Modelmentioning

confidence: 99%

“…For practical applications, space-based imaging satellites normally require agility in manoeuvring between image collection attitudes [14,15,16,17,18,19,20], because the time of each collection region in the sensor field-of-view is quite limited, the productivity of imaging satellites directly depends on the manoeuvring agility. Previous study of the natural frequency optimisation of the "roll-up" PV solar array [21,7] demonstrated that the first vibration mode of the cantilevered solar array involves an up-down cantilever motion, causing the solar array to be prone to bending once it is excited, which makes the behaviour of the solar array subjected to bending of interest to study.…”

Section: Introductionmentioning

confidence: 99%

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Computational and experimental study on dynamic instability of extended bistable carbon/epoxy booms subjected to bending

Viquerat

2018

Composite Structures

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Section: Finite Element Model Formulationmentioning

confidence: 99%

Section: Single Boom Modelmentioning

confidence: 99%

Section: Single Boom Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Computational and experimental study on dynamic instability of extended bistable carbon/epoxy booms subjected to bending

Viquerat

2018

Composite Structures

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“…Carbon fiber composite materials are widely used for higher stiffness and lower weight compared with traditional materials. The carbon fiber collapsible hinge is currently applied in many aerospace structures, such as frame of solar array and deployable structure of satellite antenna [1][2][3]. Stiffness and stability of this structure are mostly concerned about during engineering application.…”

Section: Introductionmentioning

confidence: 99%

Optimal design of carbon fiber collapsible hinge for space application

Hua¹,

Beibei²

2018

Vib. proced.

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In order to design the optimal size of carbon fiber collapsible hinge for space engineering application, the modal and folding analysis of carbon fiber collapsible hinge is carried out in this paper. Natural frequencies and mode shapes are investigated through finite element model. The result is also verified by modal experiments. The maximum stress during folding process of the hinge is obtained by quasi-static simulation analysis. In order to increase the stiffness and stability of this collapsible structure, the fundamental frequency and maximum stress are optimized with respect to the hinge size. A co-simulation optimal design method is proposed in this paper. The optimal hinge size is obtained through non-dominated sorting genetic algorithm based on radial basis function neural network surrogate model. The fundamental frequency is increased by 12 %, while the maximum stress is decreased by 13 % after optimal design.

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Experimental validation study on snap through and coiling up of deployable composite shells

Chang,

Zhao,

et al. 2023

Polymer Composites

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Bistable reeled composite shells (BRCS) have been widely used in deployable space structures due to advanced properties of light weight and large volume reduction. A finite element simulation and experimental validation to study the transition of BRCS between their two stable states are performed. In this article, multiscale representative volume element (RVE) modeling is used to compute the equivalent mechanical properties of carbon/epoxy plain woven fabrics that were utilized to construct the deployable composite laminates, followed by experimental verification. The deformation characteristics and strain energy distribution of the deployable composite shell (DCS) during snap through and coiling up are investigated using finite element analysis (FEA) and verified by strain‐gauge and digital image correlation (DIC) tests. The results show that the strain energy distribution in the snap through and coiling up of the carbon/epoxy plain woven BRCS with laminate stacking sequence of [+45/−45] is approximately symmetric. Additionally, an offset phenomena is observed during the coiling up of the BRCS in the finite element modeling. A parametric analysis is complemented to investigate effects of fiber angles on the deformation characteristics and strain energy distribution of the shell structures during snap through and coiling up.Highlights Shell deformation during snap through and coiling up was investigated. DIC test was performed to capture the shell deformation. Strain energy distribution of the deployable composite shell was discussed. Offset phenomena are observed during the coiling up.

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Natural frequency optimization of braided bistable carbon/epoxy tubes: Analysis of braid angles and stacking sequences

Cited by 29 publications

References 31 publications

Computational and experimental study on dynamic instability of extended bistable carbon/epoxy booms subjected to bending

Computational and experimental study on dynamic instability of extended bistable carbon/epoxy booms subjected to bending

Optimal design of carbon fiber collapsible hinge for space application

Experimental validation study on snap through and coiling up of deployable composite shells

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