Investigation of the Parameters of the Controlled Motion of a Descent Vehicle with an Inflatable Braking Device

Abstract

One of the promising areas of space research is the delivery of a container with a payload both during an interplanetary mission and from the Earth's orbit. This can be soil samples mined on the planets of the solar system, or the results of experiments in orbit. To deliver cargo, it is necessary to ensure controlled movement of the descent vehicle in the planet's atmosphere. The article considers the possibility of using inflatable structures for braking and controlling a spacecraft in the planet's atmosphere, as well as parrying disturbing environmental factors. A mathematical model of the movement of the descent vehicle was constructed, which was used to analyze the balancing angles of attack that occur when the payload is deflected. The results obtained using a mathematical model made it possible to determine the overloads acting on the descent vehicle during controlled motion, as well as to determine the hinge moments and calculate the parameters of the descent vehicle trajectory for various atmospheric entry conditions. The data obtained as a result of the research make it possible to draw a conclusion about the possibility of using such descent vehicles, to formulate requirements for the mechanical part of the structure during design.