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.
The paper analyzes the conditions under which a two-dimensional formulation of the thermal conductivity problem for a correct assessment of the large elastic elements temperature shock effect on the rotational motion of a small spacecraft is insufficient. Numerical simulation was carried out for a scheme of a small “Aist-2D” spacecraft. The results of this work can be used in modeling the rotational motion of a small spacecraft taking into account the temperature shock of large elastic elements.
This article considers the issues of reducing the angular velocity of rotation for a small spacecraft operated in uncontrolled flight. A mathematical model based on Euler’s dynamic equations in the main coupled coordinate system of a small spacecraft has been constructed. The transition of the inertia tensor of the Aist small spacecraft pilot model from the bench coordinate system to the main connected coordinate system was performed. A study and evaluation of the significance of various disturbing factors in modeling the rotational motion of a small spacecraft around the center of mass has been carried out. At the same time, gravitational, aerodynamic and magnetic disturbing factors are considered. The application of the -Bdot algorithm by magnetic executive bodies to reduce the angular velocity has been studied. Results are obtained demonstrating the effectiveness of the -Bdot algorithm application on the example of the Aist small spacecraft pilot model. The results of the presented work can be used in the development of effective algorithms for controlling the movement of a small spacecraft around the center of mass in order to reduce the angular velocity of its rotational motion.
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