Abstract
The article considers the idea of reducing littering the near-Earth space by means of spent stage jettisons into the Earth's atmosphere. A solution to the problem of optimization of the apsidal impulse transfer between the reference circular orbit of an Earth’s artificial satellite and the final elliptical orbit is proposed. A parametric analysis of the obtained solutions is performed, a simple pulse choice scheme close in functionality to the optimal one is proposed. Questions about the optimal number and location of pulses and the optimal mass of the first stage are investigated. An assessment of the additional mass consumption associated with the stage jettisons into the atmosphere comparing with the simple separation of the stages is performed. It was found that in the case of optimal fuel distribution among the tanks such mass consumption is small when a final ascent pulse is 1.5 km/s.
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