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Evaluating power mass characteristics of active systems for space objects de-orbit from low earth orbits

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Product Description

Three versions of active system for space objects (SO) de-orbit in which structure the electric propulsion system enters are considered: a single-stage space craft (SC) with acquisition system, two-stage SC with use as the second stage the maneuvering microsatellite with in addition established manipulator intended for accommodation SO on its board, and a mine-sweeper of small space debris. In the latter case the offered solution of system for SO deorbit will supply overlapping of a passive and active methods of the gathering the particles of small space debris with active large SO de-orbit to the dense atmosphere where there will be their combustion. With application of the developed techniques power mass characteristics of active system are calculated and their evaluating depending on an arrangement and mass orbital altitude SO, subject to de-orbit is given. Recommendations concerning types of launch vehicles for the injection of systems for de-orbite on a scheduled orbit and types of electric thrusters used in their structure are given.

Additional Information

Authors

Дронь Н.М., Дубовик Л.Г., Хорольский П.Г.

Year of publication

2015

7

Volume

124

Language

Russian

Types of files

pdf

Section

Aerospace Engineering

Quality

excellent

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