Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Simulation of landing vehicle dynamic motion in the final stage of landing

Published: 10.06.2020

Authors: Koryanov V.V.

Published in issue: #6(102)/2020

DOI: 10.18698/2308-6033-2020-6-1989

Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control

When designing promising spacecrafts and missions to explore the planets of the Solar system, preliminary testing of all the important systems affecting the success of the space mission is necessary. Among the other systems responsible for the functioning of the spacecraft, it is necessary to distinguish the landing system. The landing stage is important and complex, since this stage is accompanied by large overloads and forces of the stick-slip nature acting on the spacecraft, their effect can be critical for the spacecraft structure. When landing the descent vehicle, it is necessary to study separately the moment of approach to the surface and the movement in the ground. The purpose of this article is to describe the methodology for modeling the motion dynamics at the final stage of movement and perform numerical studies of the descent vehicle motion dynamics at the final stage of movement in the case of a hard landing. Studies were conducted for different initial conditions of approach to the surface. As a result, the values of the arising overloads acting on the descent vehicle were obtained. The data provided by the simulation allow making conclusions about the most dangerous landing options that should be considered for the successful completion of future missions.

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