Modelling of CubeSat satellite motion with inflatable braking device. Part 2. Analysis of the thermal and stress-strain state of the inflatable braking device shell

The article is devoted to the strength analysis of the inflatable spherical shell of the braking device of the CubeSat 1U microsatellite during its descent from the working orbit altitude of 500 km to the upper atmosphere of the Earth. During the flight process, the shell is subjected to thermal and force effects. To analyse the behaviour of the shell, an approach has been developed that combines the interrelated processes of numerical simulation of thermal and force loading. Modelling was performed using Ansys Static Structural and Ansys Transient Thermal software packages, as well as analytical methods for calculating heat transfer with space factors. As a result of the analysis, graphical dependencies of temperature and stresses of the shell during the descent process were obtained, the dependencies obtained allowed to analyse the change in the safety margin of the shell, which was used to determine the value of the trajectory height at which the shell failure occurs. The obtained results allow us to assess the need for structural changes in the force scheme of the shell.
EDN: XCLGSD, https://elibrary/xclgsd

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