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Spacecraft Transfer Optimization with Releasing the Additional Fuel Tank and the Booster to the Earth Atmosphere

  • NONLINEAR SYSTEMS
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Abstract

This paper considers the idea of reducing the debris of near-Earth space by releasing the spent parts of a spacecraft on orbits touching the conditional boundary of the Earth’s atmosphere. We optimize the spacecraft transfer trajectory from a circular reference orbit of an artificial Earth satellite to a target elliptical orbit in a modified pulse problem statement. The convergence of Newton’s method is improved by introducing a series of auxiliary coordinate systems at each point of applying an impulse action. The derivatives in the transversality conditions are calculated using a special numerical-analytical differentiation technique.

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Fig. 1.

Notes

  1. The numerical-analytical differentiation project is available at http://mech.math.msu.su/~iliagri/ex_value.htm.

  2. More exactly, “extremal” since the first-order optimality conditions (the Lagrange principle) are verified without considering the second-order conditions and sufficient conditions.

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Authors and Affiliations

  1. Moscow State University, Moscow, Russia

    I. S. Grigoriev

  2. Moscow State University, Baku Branch, Baku, Azerbaijan

    A. I. Proskuryakov

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  1. I. S. Grigoriev
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  2. A. I. Proskuryakov
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Correspondence to I. S. Grigoriev or A. I. Proskuryakov.

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This paper was recommended for publication by A.A. Galyaev, a member of the Editorial Board

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Grigoriev, I.S., Proskuryakov, A.I. Spacecraft Transfer Optimization with Releasing the Additional Fuel Tank and the Booster to the Earth Atmosphere. Autom Remote Control 84, 211–225 (2023). https://doi.org/10.1134/S0005117923030062

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