Thermally Induced Dynamics of a Spinning Spacecraft with an Axial Flexible Boom

Shen, Zhenxing; Hu, Gengkai

doi:10.2514/1.a33116

Cited by 25 publications

(7 citation statements)

References 12 publications

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“…The relatively small mass of a small spacecraft in the presence of large elastic elements in its composition is the reason for the significant influence of oscillations of elastic elements on the orbital motion of the spacecraft. Tests of promising new ROSA solar panels on the international space station [15,16] confirmed the seriousness of this problem. Periodic immersion of a small spacecraft in the shadow of the Earth and exit from it contribute to the occurrence of temperature shock.…”

Section: Introductionmentioning

confidence: 84%

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Modeling the deformation of an elastic element of a small spacecraft in its plane during temperature shock

2023

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A basic mathematical model of the deformation of a large elastic element of a small spacecraft in its plane is constructed. Deformations are caused by a temperature shock after a small spacecraft leaves the Earth’s shadow on the solar portion of the orbit. The model is used to conduct a computational experiment with the aim of assessing perturbations acting on a small spacecraft due to temperature shock. The temperature distribution during thermal shock is described by a one-dimensional model of thermal conductivity. The classical theory of thin plates is used to determine the deformations. The results of the estimation of disturbing factors are obtained as a result of a computational experiment for a model small spacecraft. These results indicate the need to compensate for the impact of temperature shock for small technological spacecraft. The data obtained can be used in the design of small space-craft for technological purposes.

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Section: Introductionmentioning

confidence: 84%

“…5 shows the distribution of the elementary volumetric force dN acting on each point of the elastic element to the left of the line 2 / a x = . It is the same for each point and, according to [15,16], is equal to:…”

Section: Point X Coordinate Y Coordinatementioning

confidence: 99%

Modeling the deformation of an elastic element of a small spacecraft in its plane during temperature shock

2023

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“…Temperature shock is a fast-dynamic phenomenon that occurs due to the appearance or disappearance of a heat flux [1-3]. A striking example of temperature shock in outer space is when a spacecraft enters into the Earth's shadow or comes out of it [4][5][6]. In this case, large elastic elements experience a temperature shock and undergo temperature deformations.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Stress-Strain State of a Rectangular Plate after a Temperature Shock

et al. 2023

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In this paper, the temperature shock phenomenon is considered. This phenomenon occurs during the operation of engineering structures on Earth and in outer space. A rectangular plate has been selected as a structural element exposed to temperature shock. It has a rigidly sealed edge and three free edges. A one-dimensional third initial boundary value problem of thermal conductivity was posed and solved to study the stress–strain state of the plate. Fourier’s law was used to solve this problem, taking into account the inertial term, since the temperature shock is a fairly fast-dynamic phenomenon. It was believed that all the thermophysical properties of the plate are constant and do not depend on its temperature. As a result, the temperature field of the plate was obtained after the temperature shock. This temperature field generates temperature stresses inside the plate, which lead to temperature deformations. To determine these deformations, the initial boundary value problem of thermoelasticity was posed and solved in this work. The Sophie Germain equation was used while solving this problem. To describe the plate, the theory of flexible plates was used, taking into account the stresses in the middle surface of the plate. Next, the accuracy of analytical solutions for the points displacement of a homogeneous plate subjected to a temperature shock was investigated. The temperature field was constructed using a numerical simulation. Functions of the displacement vector components were obtained using approximate analytical solutions. The accuracy of approximate analytical solutions for the components of the plate points deformation vector was estimated. The obtained results allow us to describe the stress–strain state of the plate after the temperature shock. The results of this work can be used in the design of engineering structures for both terrestrial and space purposes in terms of stability calculations and the implementation of deformation constraints.

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“…T HE uncoupled and coupled thermal-structural analysis models have been employed extensively to study thermally induced vibrations of spacecraft appendages [1][2][3][4][5]. The uncoupled model assumes that the absorbed solar flux for the structure surface is not affected by thermally induced motions (i.e., neglecting the coupling effect between structural deformations and incident heating); however, the coupled model includes the effect [1].…”

Section: Introductionmentioning

confidence: 99%