Deployment analysis of a self-deployable composite boom

Soykasap, Omer

doi:10.1016/j.compstruct.2008.08.012

Cited by 74 publications

(24 citation statements)

References 11 publications

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“…However, explicit time integration is stable only if the Courant condition is satisfied [17,18]: essentially, the time increment cannot be larger than the time for a wave to travel between adjacent nodes in the finite element mesh. Abaqus/Explicit includes damping effects and estimates the stable time increment limit at each time increment from the approximate relationship [ (9) where the wave speed is…”

Section: Abaqus/explicit Simulation Techniquesmentioning

confidence: 99%

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Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Mallikarachchi

Pellegrino

2011

Journal of Spacecraft and Rockets

114

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Deployable structures made from ultrathin composite materials can be folded elastically and are able to selfdeploy by releasing the stored strain energy. This paper presents a detailed study of the folding and deployment of a tape-spring hinge made from a two-ply plain-weave laminate of carbon-fiber reinforced plastic. A particular version of this hinge was constructed, and its moment-rotation profile during quasi-static deployment was measured. The present study is the first to incorporate in the simulation an experimentally validated elastic micromechanical model and to provide quantitative comparisons between the simulations and the measured behavior of an actual hinge. Folding and deployment simulations of the tape-spring hinge were carried out with the commercial finite element package Abaqus/Explicit, starting from the as-built unstrained structure. The folding simulation includes the effects of pinching the hinge in the middle to reduce the peak moment required to fold it. The deployment simulation fully captures both the steady-state moment part of the deployment and the final snap back to the deployed configuration. An alternative simulation without pinching the hinge provides an estimate of the maximum moment that could be carried by the hinge during operation. This is about double the snapback moment.

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Section: Abaqus/explicit Simulation Techniquesmentioning

confidence: 99%

“…2. Avariant of this hinge design, with three slots, was analyzed with the implicit finite element code Abaqus/Standard, by Yee and Pellegrino [8] and Soykasap [9]. Also, each folding section of the MARSIS booms [10] is, in fact, a tape-spring hinge with two slots with enlarged round ends.…”

mentioning

confidence: 99%

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Mallikarachchi

Pellegrino

2011

Journal of Spacecraft and Rockets

114

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“…Thin-walled deployable composite boom (DCB) structures of hinge and lenticular boom varieties are of considerable interest in the aerospace field, with typical examples shown in Figure 1 [1][2][3][4][5][6] .…”

Section: Introductionmentioning

confidence: 99%

Thermal analysis of thin-walled deployable composite boom in simulated space environment

Bai

Shenoi

Xiong

2017

Composite Structures

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This paper seeks to investigate thermal behaviour of a thin-walled deployable composite boom (DCB) in a space environment using ground thermal-vacuum test and FEA methods. Thermal tests simulating a space environment include three key conditions, namely ultra-high level of vacuum (lower than 10 -5 Pa), heat sink (-180℃) that is realized using black panels with the liquid-nitrogen cooling system and thermal loading that is achieved through infrared lamps. The thermal tests of the DCB under seven typical heat fluxes were conducted to characterize heat transfer mechanisms and to obtain temperature fields. The basic heat transfer methods for the DCB in a space environment were surface radiation, cavity radiation and heat conduction. These led to significant temperature difference and gradient occurring on the irradiated and shadowed parts of the DCB at nighttime and daytime. FE models were established to predict temperature fields and thermally induced deformation. Good correlation was achieved between experimental and numerical results.

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“…Storable tubular extensible members (STEMs) have been widely investigated for many years as technological solution for numerous space applications [1][2][3][4][5]. STEMs are considered for stabilization systems via gravity gradient in low orbit spacecrafts [6,7], self-deployable antennas [8], and deployable booms for solar sails [9,10].…”

Section: Introductionmentioning

confidence: 99%

Nonlinear buckling and folding analysis of a storable tubular ultrathin boom for nanosatellites

Barbera

Laurenzi

2015

Composite Structures

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In this work we investigated the stability behavior and the folding capability of an ultrathin tubular composite boom with C-cross section to be used in nanosatellites applications. A nonlinear buckling analysis was performed using the Riks method, adopting a perturbed finite element model to study the influence of the unavoidable geometrical variations of the boom thickness, arising from the composite manufacturing processes, on the stability behavior of the tubular structure. The effect of several levels of geometrical imperfection on the buckling behavior was analyzed. The minimum coil radius that can be used for a safe storage the boom was determined by quasi-static explicit analysis. The boom folding process was considered as formed by two sequential steps, the flattening and the coiling. The stress fields associated with both steps were investigated.

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Deployment analysis of a self-deployable composite boom

Cited by 74 publications

References 11 publications

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Thermal analysis of thin-walled deployable composite boom in simulated space environment

Nonlinear buckling and folding analysis of a storable tubular ultrathin boom for nanosatellites

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