Оценка параметров управляемого движения спускаемого аппарата с надувным тормозным устройством путем отклонения элементов конструкции

Abstract

Currently, there is a constant development and improvement of space technology. One of the promising areas of space research is the delivery of a container with a payload both in an interplanetary mission and from the Earth’s orbit. The cargo could include soil samples mined on the planets of the solar system, or the results of experiments in orbit. To deliver the cargo, it is necessary to ensure controlled motion of the descent vehicle in the planet’s atmosphere. The paper considers the possibility of using inflatable devices for braking and controlling a spacecraft in the planet’s atmosphere, as well as for perturbational control. A mathematical model of the descent vehicle motion was developed, which was used to analyze the balancing angles of attack that occur when the payload is deflected. The results obtained made it possible to determine the overloads acting on the descent vehicle during controlled motion, determine the hinge moments, and calculate the parameters of the descent vehicle trajectory for various atmospheric entry conditions. Findings of the research show the possibility of using such descent vehicles and allow us to formulate design requirements for the mechanical part of the structure.