Analysis of the design of the drag braking device for CubeSat satellites for withdrawal from low near-Earth orbits
Clogging near-Earth outer space by spacecrafts that have failed is a threat of collision with functioning objects in space. To solve the problem of man-made debris, which may affect the development of cosmonautics in the future, a lot of collision avoidance maneuvers are proposed. The most feasible method is to use spherical braking devices providing a predictable descent of the satellite from the orbit, regardless of the orientation of its body, and the shortest time of departure from low earth orbits. Based on the results of the system analysis, the rational composition and configuration design of the device using spherical brake shells for deorbiting CubeSat nanosatellites from low Earth orbits were determined, taking into account the mass and size limitations of the standard 1U CubeSat module.
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