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For various missions that are currently being designed and planned at the present time, it is necessary to ensure reliably the stage of landing on the surface of the planet. Among the currently proposed devices that help to perform the landing of the landing vehicle, a separate interest is inflatable devices. Using inflatable device instead of rigid device has advantages, such as a small mass and a great compacity. Studies have focused on the angular motion of landing vehicles entering the atmosphere, with allowance of small asymmetries. During the descent in the atmosphere, the landing vehicle and its braking device are subjects to important perturbations, due to external environment. Thus, the inflatable device can be deformed, due to its flexibility, and the movement can become unstable. In the paper is analyzes the movement of such a landing vehicle, which uses such special devices made of inflatable devices. The paper is devoted to the analysis of movement at the final stage of landing - approaching the surface, touching the surface and further interaction with the surface. As a result, it is concluded that the most unfavorable approach to the surface, when the resulting overload is of the greatest importance.

The problem of accumulation of space debris in near-Earth space is very relevant now. More than 15,000 debris have been recorded, and this represents a danger for current and future missions to space. A solution to this issue is to remove these spacecrafts from orbit. One of the ways to do it is to use inflatable device. These inflatable braking device can be installed on the landing vehicles on Earth, before their launch, or after they have been labelled as space debris. Studies have already been conducted about inflatable device. Using inflatable device instead of rigid device has advantages, such as a small mass and a great compacity, which is convenient to respect the required launching volume. This paper is dedicated to use of various inflatable brake devices and they are compared with each other.

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A brief introduction to the meaning of on-orbit services and research on space-based services is provided in this work. In the context of on-orbit service, the near-circular orbit is idealized as a disturbed circular orbit, and a general equation for the optimal maneuver of the near-circle orbit is presented. The examples of coplanar on-orbit services in low, medium and high orbits are analyzed respectively, and the best maneuvering scheme for orbit transfer is solved by special software. Further analysis of the impact of different heights of parking orbit on the optimal maneuvering scheme reveals that the closer parking orbit to the target orbit, the less energy is required for maneuvering, but the phase-modulation time and the transport capacity of the launch vehicle should be considered comprehensively.