Consideration of the Initial Deformation From Natural Oscillations of Large Elastic Elements of the Spacecraft When Assessing Microaccelerations From Thermal Shock Using a Two-dimensional Model of Thermal Conductivity

Sedelnikov, A. V.; V.V., Serdakova; S.V., Glushkov; Nikolaeva, Alexandra; M.A., Evtushenko

doi:10.1007/s12217-022-09938-3

Cited by 3 publications

(9 citation statements)

References 19 publications

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“…However, for the development of a control algorithm, where various scenarios should be provided, such a statement is not enough. Therefore, in this paper, we use the two-dimensional formulation of the thermoelasticity problem described in [25,34,52]. It is different from the one-dimensional one because the initial deformed state of the solar panel at the time of the temperature shock is taken into account.…”

Section: The Problem Of Thermoelasticitymentioning

confidence: 99%

“…Mathematically, the two-dimensional thermoelasticity problem is represented by the following system of equations [25,34,52]:…”

Section: The Problem Of Thermoelasticitymentioning

confidence: 99%

“…u z0 in Figure 2 refers to the maximum deviation of the free edge of the flexible element at the initial deflection. More significant values of u z0 than shown in Figure 2 can cause a stability loss of the flexible element [34,53] and have not been considered in this work.…”

Section: Numerical Modelingmentioning

confidence: 99%

“…These requirements are becoming increasingly high over time due to the increase in remote sensing resolution [32,33]. In many works, for example [34,35], the authors indicate that temperature shock can violate the orientation requirements. This is especially true of the requirements for the angular velocity of the small spacecraft rotation at the time of remote sensing of the Earth [36,37].…”

Section: Introductionmentioning

confidence: 99%

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Investigation of Perturbations Arising from Temperature Shock with a Symmetrical Arrangement of Flexible Elements of a Small Spacecraft

Bormotov

Orlov

2023

Symmetry

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This paper investigates the effect of a temperature shock on a small spacecraft with symmetrically arranged flexible elements. A two-dimensional thermoelasticity problem is posed. The disturbing effect of temperature shock on a small spacecraft has been determined. The assessment of the main disturbing factors arising from the temperature shock of flexible elements of a small spacecraft was carried out. Approximate dependences were obtained for the components of the displacement vector of the flexible element points. Numerical simulation was carried out for the symmetric scheme of the small spacecraft with two and four flexible elements. The dependence of the inertia force on temperature shock for the simulated small spacecraft at various initial deflections of the flexible element was constructed. Conclusions were drawn about the significance of the temperature shock influence on the dynamics of a small spacecraft. The results obtained were compared with the results of other studies and can be used in solving problems of remote sensing of the Earth and the implementation of gravity-sensitive processes on board small spacecraft.

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Section: The Problem Of Thermoelasticitymentioning

confidence: 99%

“…Mathematically, the two-dimensional thermoelasticity problem is represented by the following system of equations [25,34,52]:…”

Section: The Problem Of Thermoelasticitymentioning

confidence: 99%

Section: Numerical Modelingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Investigation of Perturbations Arising from Temperature Shock with a Symmetrical Arrangement of Flexible Elements of a Small Spacecraft

Bormotov

Orlov

2023

Symmetry

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“…To assess the impact of thermal shock on the efficiency of completion of the tasks, it is not necessary to consider the dynamics of thermal shock [18][19][20]. It is enough to describe the most dangerous case and estimate the maximum deformations of the solar panel.…”

Section: Introductionmentioning

confidence: 99%

Estimation of Maximum Temperature Deformations of Solar Panels of Earth Remote Sensing Small Satellite “Aist-2D”

Serdakova

2023

Advances in Transdisciplinary Engineering

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This article evaluates the temperature deformations of a solar battery panel of a small satellite “Aist-2D” designed for the Earth remote sensing as a result of a thermal shock. Such an assessment is necessary for successful performance of the target tasks of remote sensing of the Earth by a small spacecraft. As a result of the temperature shock, the orientation requirements of the spacecraft may be violated. This is especially true for the angular velocity requirements. The maximum deflection of solar panel is estimated using a one-dimensional thermoelasticity model. The incident heat flux is assumed to be perpendicular to the surface of the solar panel. The panel itself has a flat, non-deformed shape at the time of the temperature shock. This situation makes it possible to estimate the maximum effect of the thermal shock. In this case, the solar panel heating will be maximal. Significance of perturbations from temperature shock leads to the need to take it into account in the analysis of orbital motion of the spacecraft. The stress-strain state of the solar panel has been investigated. The dependences of the deflection of the solar panel points during the temperature shock are obtained. The results of the estimation can be used to assess the impact of thermal shock on the task execution of “Aist-2D”.

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The Symmetric Formulation of the Temperature Shock Problem for a Small Spacecraft with Two Elastic Elements

et al. 2023

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The paper considers the problem of a small-spacecraft elastic elements’ temperature shock that occurs when the spacecraft immerses into the Earth’s shadow or comes out of it. A small spacecraft with two elastic elements is simulated. In the first approximation, such a problem is considered to be a symmetric problem. Estimations of disturbing factors from the temperature shock in a symmetric formulation are obtained. The differences from the results for a small spacecraft with a single elastic element are analyzed. The results of the work can be used for promising small technological spacecraft development, as well as for solving problems of space debris removal and remote sensing of the Earth.

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Consideration of the Initial Deformation From Natural Oscillations of Large Elastic Elements of the Spacecraft When Assessing Microaccelerations From Thermal Shock Using a Two-dimensional Model of Thermal Conductivity

Cited by 3 publications

References 19 publications

Investigation of Perturbations Arising from Temperature Shock with a Symmetrical Arrangement of Flexible Elements of a Small Spacecraft

Investigation of Perturbations Arising from Temperature Shock with a Symmetrical Arrangement of Flexible Elements of a Small Spacecraft

Estimation of Maximum Temperature Deformations of Solar Panels of Earth Remote Sensing Small Satellite “Aist-2D”

The Symmetric Formulation of the Temperature Shock Problem for a Small Spacecraft with Two Elastic Elements

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