Assessing the feasibility of small spacecraft angular velocity requirements taking into account temperature shock


Аuthors

Sedel'nikov A. V.*, Nikolaeva A. S.**, Serdakova V. V.***

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: axe_backdraft@inbox.ru
**e-mail: ezhevichka333@gmail.com
***e-mail: valeriay.121@yandex.ru

Abstract

The main purpose of the work consists in evaluating the requirements feasibility for target values ensuring of angular velocity of a small Earth remote probing spacecraft with account for the temperature shock.

The temperature shock phenomenon of solar panels occurs while a spacecraft movement from the Earth shadow to the sunlit parts of the orbit or, vice versa, when it enters the Earth shadow. In these cases, the heat flux from the Sun sharply changes, which significantly affects the bulky elastic elements (solar panels, radiators, antennas, etc.) of the spacecraft. Thus, the exit from the Earth shadow is accompanied, for example, by the heat flux origination, and dashing heating of bulky elastic elements. Heating, in its turn, leads to their temperature deformations. This factor is the cause of perturbations that affect the spacecraft motion, especially when it comes to a small spacecraft, since in this case mass ratios of bulky elastic elements to spacecraft the total mass are much higher. Thus, the studies of temperature shock for a small spacecraft are most relevant.

Analysis of a number of studies reveals that the temperature shock phenomenon leads to the accuracy decrease of a small Earth remote probing spacecraft guidance at the target object, and reduces the quality of the target task performing. In separate cases, there was even talk of possible stability loss of a spacecraft itself.

The article deals with the of temperature shock impact of solar panels within the framework of one-dimensional heat conduction model. A thin plate is being used as a first approximation model of solar panels. A 1D thermoelasticity problem has been set to study the stress-strain state of the plate. This problem solution is the of the plate middle layer deflection occurring due to temperature shock.

The dependences of perturbing factors on the temperature shock were obtained in this work. The motion parameters of a small spacecraft resulting from these perturbations were estimated.

Numerical modeling was performed with the Wolfram Mathematica for the EO-1 small Earth remote probing spacecraft.

As the result of the research, the values of angular velocity of the EO-1 small spacecraft were evaluated and the feasibility of angular velocity requirements for modern small Earth remote probinng spacecraft was analyzed. The results of the work may be employed in performing Earth remote probing tasks by small spacecraft.

Keywords:

temperature shock, solar panel, small spacecraft, perturbing moment, angular acceleration

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