Modeling the Effect of a Temperature Shock on the Rotational Motion of a Small Spacecraft, Considering the Possible Loss of Large Elastic Elements Stability

Sedelnikov, A. V.; Serdakova, Valeria; Orlov, Denis; Nikolaeva, Alexandra; Evtushenko, Maxim

doi:10.1007/s12217-022-09997-6

Cited by 8 publications

(11 citation statements)

References 20 publications

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“…This model assumes that all thermophysical properties of the MA2 material remain constant over the entire temperature range. The temperature ranges from 200 K (initial temperature) to approximately 300 K [4,9,25]. This range is not wide enough to take into account changes in thermophysical properties.…”

Section: Main Results Of Researchmentioning

confidence: 99%

“…Violation of these restrictions can decrease the quality of shooting of the target objects [4][5][6]. The thermal shock on big elastic elements of the structure of a small spacecraft is one of the factors that can violate the accuracy of orientation [7][8][9]. Such elements of a small the Earth remote sensing satellite are solar panels [10][11][12].…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Main Results Of Researchmentioning

confidence: 99%

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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“…The damage process in the form of graphs of changes in interlaminar normal stresses across the plate width depending on the axial deformation is shown in figure 4. As can be seen from the figure 4, interlaminar normal stresses near the free edge reach a maximum value Since the stratification process using the bilinear CZM model is non-linear, the introduction of a fictitious astringency determined by the damping parameter helps to avoid convergence problems [7,8]. At the same time, by varying the parameter E from 0 to 1, it is possible to increase the effect of shear stresses on the delamination and, accordingly, on the form of the bilinear diagram (figures 5 and 6).…”

Section: Numerical Solutionmentioning

confidence: 99%

Estimation of Composites Delamination due to the Edge Effect

Evtushenko,

Skvortsov,

Khnyryova

2023

Advances in Transdisciplinary Engineering

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The paper investigates the possibility of delamination near the free edges of composites is investigated by the example of a two-dimensional formulation of the Pipes-Pagano problem. A bilinear material damage law based on the cohesive zone model (CZM) is considered. An example of selecting the stiffness of a cohesive layer is given, and a calculation of a laminated composite by the finite element method in the ANSYS program is performed. The method used makes it possible to determine the concentration of interlaminar stresses due to the edge effect, and, using a special set of interface elements simulating mating surfaces and following process of delaminaton, to investigate the composite delamination. When interface elements are added, the problem becomes non-linear and the solution in a two-dimensional formulation significantly reduces labor intensity and simplifies modeling, and also allows you to specify a large number of elements over the thickness of each layer. The problems with the convergence of the solution that have arisen can be eliminated with the help of special numerical modeling techniques and by varying the parameters embedded in the program. The revealed damage to the cohesive layer due to the edge effect can lead to delamination and premature failure of composites. The presented results can be used in the design of products from composite materials in rocket and space technology.

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“…As a rule, gravity-sensitive processes are energy intensive [2,4,8,14,15,[28][29][30]]. This, for example, led to the fact that the design and layout diagrams of technological spacecraft of the Foton series for the first spacecraft of the series were devoid of solar panels and used only battery power [3,5,31,32].…”

Section: Analysis Of the Design Appearance Of A Small Technological S...mentioning

confidence: 99%

Analysis of the requirements for microaccelerations and the design appearance of a small spacecraft for technological purposes

Taneeva

2023

E3S Web of Conf.

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The article analyzes the possibility of implementing gravity-sensitive technological processes on board a small technological spacecraft. The requirements for microaccelerations imposed by the physical features of the flow of gravitation-sensitive processes are presented. The advantages and disadvantages of using small spacecraft for space technologies are analyzed. The design image of a small spacecraft for technological purposes is presented.

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Modeling the Effect of a Temperature Shock on the Rotational Motion of a Small Spacecraft, Considering the Possible Loss of Large Elastic Elements Stability

Cited by 8 publications

References 20 publications

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

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

Estimation of Composites Delamination due to the Edge Effect

Analysis of the requirements for microaccelerations and the design appearance of a small spacecraft for technological purposes

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