Speaker
Description
Through space exploration, we gain a new perspective to study Earth and the solar system. The number of missions based on the study of the surface and interior of the planets are increasing every year, and the aerobraking phenomena are inevitable when we are very close to a planet atmosphere. On the other hand, several missions to other planets have already exploited aerobraking, in order to save the amount of propellant carried and therefore optimize vehicle design mass.
Since the Antenna is located on the external part of the spacecraft, it is greatly affected by the heat generated during the aerobraking maneuvers and dedicated analyses are needed in order to predict the antenna thermal performance throughout the entire time.
From an industry point of view, phase A and B analyses must be performed rapidly and reliably taking into account the tight project schedule. The purpose is to successfully design all the antenna items to withstand the aerodynamic forces and heating associated with the entry velocities, as well as to develop dedicated technologies to optimize the overall antenna performances.
The most important analysis is to predict the nominal temperatures for the next orbit drag pass, but also to identify those antenna orientations or spacecraft attitudes that define the technological limits of the antenna. This allows the spacecraft GNC (guidance & navigation control) team to effectively plan the correct maneuvers and drag pass without an excessive heating of the antenna.
The proposed approach is to use a commercial software, without the need to develop dedicated subroutines or interleave multiple packages. The data presented will show how to have a comprehensive Antenna temperature prediction, based on the spacecraft position, as well as the density and velocity at different trajectory points. #
