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

Abstract

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.

Method of taking into account influence of thermal shock on dynamics of small satellite and its use in analysis of microaccelerations

“…For numerical simulation according to a symmetrical scheme (Figure 2b), we will choose a small satellite for remote sensing of the Earth Aist-2D [29], keeping the main parameters of the material of solar panels, which were presented in Table 1. In this case, the application of the principle presented in the article presents "significant" influence of thermal shock from the point of view of the functional principle and the symmetrical scheme of a small satellite from the point of view of the geometric principle.…”

“…A number of target tasks are associated with the need for accurate orientation of a small satellite (problems of remote sensing of the Earth from space) or limitations of the microacceleration field of the internal environment of a small satellite, especially the area of equipment's location [26,27] (problems of implementing gravitationally sensitive processes on board a small satellite). Other tasks allow the operation of a small satellite in non-oriented flight [28,29], for example, measuring the parameters of the space environment. Therefore, it is necessary to make sure that the thermal shock of large elastic elements of a small satellite can degrade the quality of its performance of target tasks.…”

“…To choose a strategy for taking into account the effect of thermal shock, it is necessary to analyze the design of a small satellite. The variety of forms of small satellites suggests the use of various models for assessing the effect of tehermal shock [29,30]. Figure 2 If a small satellite has one large elastic element (Figure 2 a), then the model for taking into account the influence can be expressed using the approximate dependences of the displacement vector components presented in the research for a one-dimensional heat conduction model [29].…”

“…The variety of forms of small satellites suggests the use of various models for assessing the effect of tehermal shock [29,30]. Figure 2 If a small satellite has one large elastic element (Figure 2 a), then the model for taking into account the influence can be expressed using the approximate dependences of the displacement vector components presented in the research for a one-dimensional heat conduction model [29]. However, a larger number of elastic elements (Figure 2 b, c, d) will complicate the construction of a model of taking into account the influence of thermal shock.…”

“…The researches carried out in the article [16] demonstrated that for a small satellite with one large elastic element (asymmetric version), the thermal shock affects the translational and rotational parts of the small satellite's motion. For a symmetrical small satellite, rotational effects will be compensated due to symmetry [29]. In this case, the thermal shock will have a greater effect on the translational part of the motion of a small satellite.…”