Investigation of possible descent trajectories for a maneuverable lander in the venus atmosphere

Abstract

It is proposed to use lifting body type of a lander, which has a permissible complication of the structure, compared with a ballistic type of a lander, and lift-to-drag ratio sufficient for solving the existing maneuvering tasks during the descent in the Venus atmosphere in order to achieve the desired landing area. Possible descent trajectories for a lander of this type are considered, including the possibility of making maximum lateral maneuver, while taking into account long-period trajectories with multiple immersions into the dense layers of the atmosphere, a comparison of these trajectories with the descent trajectory of a traditionally used ballistic type of a lander is also made. The use of a maneuverable lander will enable wide outreach of landing areas, as well as decrease the acting loads and widen the range of scientific tasks and research being carried out.