Experimental Verification of Thermal Structural Responses of a Flexible Rolled-Up Solar Array

Lee, Hangseo; Yamasaki, Miho; Murozono, Masahiko

doi:10.2322/tjsass.56.197

Cited by 2 publications

(2 citation statements)

References 8 publications

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“…Using finite element analysis, the results showed the correct forecast of the thermal snap phenomenon observed in the solar panel experiments. Other notable successful experiments include the works by Iwata et al (2011) for Advanced Land Observing Satellite solar array and Lee et al (2013) for HST's solar array by using smaller scaled models in their investigations. The comparison of the analytical solution, finite element analysis and experiment result revealed that the short term transient of the temperature difference during eclipse transition was important for simulating the TID of the solar array.…”

Section: Introductionmentioning

confidence: 99%

“…Their deployable solar panels' size is much smaller Figure 1 The in-orbit thermal environment of a satellite compared to model parameters in previous studies made, which means the effect might be small too. Nonetheless, the aforementioned experiments on the scale model show that the problem could still be induced (Iwata et al, 2011;Johnston and Thornton, 2000;Lee et al, 2013). Furthermore, in anticipation of future advanced mission requirements, prior investigation regarding TID is worthwhile so that necessary counter-measures can be implemented if required.…”

Section: Introductionmentioning

confidence: 99%

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Thermally induced dynamics of deployable solar panels of nanosatellite

Ibrahim

Yamaguchi

2019

AEAT

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Purpose This study aims to predict the types of thermally induced dynamics (TID) that can occur on deployable solar panels of a small form factor satellite, CubeSat which flies in low Earth orbit (LEO). The TID effect on the CubeSat body is examined. Design/methodology/approach A 3U CubeSat with four short-edge deployable solar panels is considered. Time historic temperature of the solar panels throughout the orbit is obtained using a thermal analysis software. The results are used in numerical simulation to find the structural response of the solar panel. Subsequently, the effect of solar panel motion on pointing the direction of the satellite is examined using inertia relief method. Findings The thermal snap motion could occur during eclipse transitions due to rapid temperature changes in solar panels’ cross-sections. In the case of asymmetric solar panel configuration, noticeable displacement in the pointing direction can be observed during the eclipse transitions. Research limitations/implications This work only examines an LEO mission where the solar cells of the solar panels point to the Sun throughout the daylight period and point to the Earth while in shadow. Simplification is made to the CubeSat structure and some parameters in the space environment. Practical implications The results from this work reveal several practical applications worthy of simplifying the study of TID on satellite appendages. Originality/value This work presents a computational method that fully uses finite element software to analyze TID phenomenon that can occur in LEO on a CubeSat which has commonly used deployable solar panels structure.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thermally induced dynamics of deployable solar panels of nanosatellite

Ibrahim

Yamaguchi

2019

AEAT

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Technologies for Increasing the Control Efficiency of Small Spacecraft with Solar Panels by Taking into Account Temperature Shock

Sedelinkov,

Nikolaeva,

Serdakova

et al. 2024

Technologies

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The problem of the effective control of a small spacecraft is very relevant for solving a number of target tasks. Such tasks include, for example, remote sensing of the Earth or the implementation of gravity-sensitive processes. Therefore, it is necessary to develop new technologies for controlling small spacecraft. These technologies must take into account a number of disturbing factors that have not been taken into account previously. Temperature shock is one such factor for small spacecraft with solar panels. Therefore, the goal of the work is to create a new technology for controlling a small spacecraft based on a mathematical model of the stressed/deformed state of a solar panel during a temperature shock. The main methods for solving the problem are mathematical methods for solving initial/boundary value problems, in particular, the initial/boundary value problem of the third kind. As a result, an approximate solution for the deformation of a solar panel during a temperature shock was obtained. This solution is more general than those obtained previously. In particular, it satisfies the symmetrical condition of the solar panel. This could not be achieved by the previous solutions. We also observe an improvement (as compared to the previous solutions) in the fulfillment of the boundary conditions for the whole duration of the temperature shock. Based on this, a new technology for controlling a small spacecraft was created and its effectiveness was demonstrated. Application of the developed technology will improve the performance of the target tasks such as remote sensing of the Earth or the implementation of gravity-sensitive processes.

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Experimental Verification of Thermal Structural Responses of a Flexible Rolled-Up Solar Array

Cited by 2 publications

References 8 publications

Thermally induced dynamics of deployable solar panels of nanosatellite

Thermally induced dynamics of deployable solar panels of nanosatellite

Technologies for Increasing the Control Efficiency of Small Spacecraft with Solar Panels by Taking into Account Temperature Shock

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