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.
The paper analyzes rotational motion of an aerial vehicle, which inertia resultant moments are not equal to each other. An ash seed served as the prototype of such an aerial vehicle, as the seed flies in the autorotation mode. Mathematical model of the aerial vehicle angular motion was compiled to study its movement. Mathematical model equations were solved by the 4th order Runge—Kutta Method using the developed software. Analysis of the results obtained made it possible to make a conclusion about the influence of the inertia moments magnitude on the transient process nature. The resulting mathematical model could be applied in studying the descent vehicle motion controlled by the payload rotation method. As a result of altering the payload angular position, as well as of deformation of the descent vehicle flexible elements, similar mass distribution could be obtained. Thus, research is being carried out to analyze conditions, under which the aerial vehicle enters the autorotation mode, and whether this effect could be applied or eliminated in technology.
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