Assessment of temperature shock impact on orbital motion dynamics of a spacecraft for technological purposes

DOI: 10.34759/vst-2019-4-200-208

Аuthors

Sedel'nikov A. V.^*, Belousova D. A.^**, Orlov D. I.^***, Filippov A. S.^****

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

*e-mail: axe_backdraft@inbox.ru
**e-mail: daryabelousova@outlook.com
***e-mail: grand_99v@mail.ru
****e-mail: filippoval89@mail.ru

Abstract

The main objective of the work is assessing the of temperature shock impact on the orbital motion dynamics of the spacecraft for technological purposes.

The problem consists in the uncertainty of center of mass displacement due to the impact of temperature shock and, thus, the motion control error. This problem is particularly relevant for the spacecraft for technological purposes, and products sensitive to the experimental conditions.

The importance of assessing the impact of temperature shock is determined by the need to ensure the spacecraft functioning with the specified parameters of motion, as well as maintaining controllability of the spacecraft in the presence of orbital eclipse periods.

Analysis of the studies by the scientists from various countries reveals that control of a small spacecraft with no large elastic elements in the design-layout scheme often reduces to the target values active control of the angular velocity of its rotation.

In this case, the orbital eclipse periods are not highlighted separately, and no changes in spacecraft movement control law are made while its immersing in and out of Earth shadow.

The article deals with the issues related to the temperature shock impact on the orbital motion change of a spacecraft for technological purposes, and modeling the scale and nature of the effect.

The temperature shock impact assessment is based on the 3D modeling of the processes occurring at the spacecraft entering and exiting the orbital eclipse period.

For a small “Return— MKA” type spacecraft the three-fold excess of admissible micro-accelerations was obtained.

As the result of the conducted study, a conclusion was made that control algorithms development, levelling the temperature shock from the viewpoint of occurring micro-accelerations compensation, was required for successful implementation of gravity- sensitive processes onboard the spacecraft for technological purposes with the orbital eclipse period.

A three-dimensional heat conduction problem was solved to determine the target parameters of control algorithms. The following simplifying assumptions were introduced to solve the problem:

– the elastic element model was a frame structure;

– the elastic element was rigidly fixed in the small spacecraft body;

– the elastic element properties satisfied the conditions of homogeneity;

– the heat flow was uniform;

– operating temperature range was −170... + 110 °C;

– the properties of the elastic element material were considered constant throughout the operating temperature range;

– orientation changing of normal to the elastic element surface due to its own oscillations was neglected.

Keywords:

spacecraft, orbital eclipse period, elastic elements, center of masses, three-dimensional heat conduction problem, boundary value problem, control algorithms

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