Deployment analysis and optimization of a flexible deployable structure for large synthetic aperture radar antennas

Wang, Yan; Guo, Hongwei; Yang, Hui; Liu, Rongqiang; Deng, Zongquan

doi:10.1177/0954410015594638

Cited by 12 publications

(4 citation statements)

References 25 publications

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“…The results of 17 design points are listed in Table 6. The fitting of response surface function with maximum difference minimization method is introduced to construct corresponding response surface model, and the complex nonlinear relationships between the objective function and design variables are approximatively expressed [16]. The objective function can be written in terms of a series basic function as follows:…”

Section: Explicit Objective Function and Constraint Functionmentioning

confidence: 99%

Analysis of mechanical properties in bending processes and optimal design of simple tape spring

Zhao

Zhang

et al. 2017

Journal of Modeling in Mechanics and Materials

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Abstract:Tape spring is straight, thin-walled, elastic strip with curved cross-section, which can replace traditional hinges by allowing for folding elastically and unfolded releasing stored energy with fewer component parts. This work is devoted to the properties of the folding and deployment of simple tape spring by numerical simulation and experiment method. Firstly, the folding process of tape spring is experimentally investigated using a specially designed test rig and verified by using nonlinear finite element ABAQUS/Standard solver. Then the moment-rotation relationships for symmetric bending are studied, the effects of subtended angle of section, total tape spring length, thickness and cross section radius on the performance of tape spring are investigated. Furthermore, the optimal model of tape spring structure design is established based on the response surface methodology (RSM) and parameter's effective analysis, which aims at maximum strain energy during the tapespring hinge deployment and subjects to allowable stress of tape spring. And the interior point algorithm is used to solve the optimal model. The optimal results are of great importance to the design of novel deployable structures with high stability, reliability and lightweight.

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Section: Explicit Objective Function and Constraint Functionmentioning

confidence: 99%

Analysis of mechanical properties in bending processes and optimal design of simple tape spring

Zhao

Zhang

et al. 2017

Journal of Modeling in Mechanics and Materials

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“…Composite materials and structures have attracted tremendous interest for their compelling advantages in a range of engineering problems that have placed heightened requirements in safety, environment, competitiveness, and cost over recent years 1 . Carbon fiber‐reinforced polymer (CFRP) is an advanced composite material known for its remarkable properties, including high specific strength and specific modulus, low coefficient of linear expansion, as well as excellent resistance to fatigue and damping 2,3 . These exceptional qualities have established CFRP as the preferred material for aerospace structures, such as satellite support frames, antenna support struts, axial engine supports, and a wide range of engineering applications 4–6 …”

Section: Introductionmentioning

confidence: 99%

Effect of delamination on the dynamic characteristics of thin‐walled carbon fiber‐reinforced polymer tube

Luo,

Yu,

Zhang

et al. 2023

Polymer Composites

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Thin‐walled carbon fiber‐reinforced‐polymer (CFRP) tubes are susceptible to damage, which impacts their dynamic characteristics. This paper investigates the influence of delamination damage on the dynamic properties of thin‐walled CFRP tubes through finite element simulation and experimental methods. A transversely isotropic principal model is employed to establish the geometric model. Delamination damage is induced using the cohesive zone model and the secondary stress criterion. Both circumferential and elliptical delamination cases are studied. The modal test is conducted using the hammer excitation method. It is observed that the finite element model aligns with the experimental results. It is discovered that the larger the delamination size, the lower the natural frequency for a given damage location. The location of the delamination within a single layer has minimal effect on the natural frequency. The natural frequency exhibits a symmetrical pattern of decreasing and then increasing as the delamination shifts from the sides toward the center layer. Positional information is discernible in the modal shape, which can be utilized for delamination detection and localization.Highlights The damage model is built by transversal isotropic equation and cohesive unit. Finite element model is built with various delamination sizes and locations for two cases. Modal tests are performed on CFRP tubes and obtained good accuracy. Effect of delamination size and location on dynamic parameters is discussed.

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“…1,2 Conventionally, deployment mechanisms have been applied to solar panels and antenna. 3,4 Representatively, a deployable antenna using the cable-net tension structure controlled by hinges 5 and cables and a large ring deployable mechanism using multiple deployable modules of six-bar linkage controlled by the cables 6 were presented and studied. These structures can maximize the storage efficiency of a launch vehicle, enabling the launch of multiple satellites.…”

Section: Introductionmentioning

confidence: 99%

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Choi

Lee

Hwang

et al. 2019

Advances in Mechanical Engineering

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This article presents a high precise deployment mechanism for a deployable space telescope to facilitate satellite miniaturization. It is designed with a passive deployment mechanism utilizing a spring hinge. In particular, the customized modules and an assembly jig are specifically designed to reduce alignment errors. To confirm the feasibility of the designed mechanism, three alignment errors that influence the optical performance of the structure-tilt, de-center, and despace-are theoretically analyzed for quarter, half, and full model, respectively. In the case of quarter model, significant results are obtained as a tilt of 21.12 mrad, a de-center of 2.20 mm, and a de-space of 1.71 mm. Based on the theoretical analysis, a deployment mechanism of the quarter model is fabricated, and the alignments of the deployment mechanism are experimentally investigated with a measurement platform consisting of five non-contact-based laser displacement sensors. In addition, the influence of gravity on the alignment error is analyzed and compensated by investigating the tendency of the alignment error according to the rotation degree of the measurement model for the direction of gravity. As a result of the gravity compensation, the proposed mechanism gives acceptable alignment errors as a tilt of 30.04 mrad, de-center of 8.92 mm, and de-space of 4.03 mm, which are controllable by employing the conventional focusing mechanism.

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Deployment analysis and optimization of a flexible deployable structure for large synthetic aperture radar antennas

Cited by 12 publications

References 25 publications

Analysis of mechanical properties in bending processes and optimal design of simple tape spring

Analysis of mechanical properties in bending processes and optimal design of simple tape spring

Effect of delamination on the dynamic characteristics of thin‐walled carbon fiber‐reinforced polymer tube

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

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