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Abstract <p>This paper considers the idea of reducing near-Earth space debris by releasing a spent additional fuel tank (AFT) and the booster’s central block into the Earth’s atmosphere. The spacecraft transfer from a reference circular orbit of an artificial Earth satellite to a target elliptical orbit is optimized. The transition maneuvers are carried out using a booster with a high limited thrust engine and the AFT. The second zonal harmonic of the Earth’s gravitational field is taken into account. A simplified model of spacecraft control is considered: the direction of the thrust vector on each of the active segments are determined by two angles that depend linearly on time.</p>

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A Simple Control Scheme for the Problem of Spacecraft Transfer into a Target Orbit with Releasing the Separable Part of Its Launch Vehicle into the Earth’s Atmosphere

  • 期刊论文

  • 发表日期：

    2025年6月1日

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  • A. Proskuryakov

摘要

Abstract

This paper considers the idea of reducing near-Earth space debris by releasing a spent additional fuel tank (AFT) and the booster’s central block into the Earth’s atmosphere. The spacecraft transfer from a reference circular orbit of an artificial Earth satellite to a target elliptical orbit is optimized. The transition maneuvers are carried out using a booster with a high limited thrust engine and the AFT. The second zonal harmonic of the Earth’s gravitational field is taken into account. A simplified model of spacecraft control is considered: the direction of the thrust vector on each of the active segments are determined by two angles that depend linearly on time.