Spacecraft transfer optimization with releasing the additional fuel tank and the booster to the Earth atmosphere

DOI10.1134/S0005117923030062zbMath1521.93127OpenAlexW4385990699MaRDI QIDQ6047933

A. I. Proskuryakov, I. S. Grigoriev

Publication date: 13 September 2023

Published in: Automation and Remote Control (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1134/s0005117923030062

zbMATH Keywords

boundary value problemspacecraftLagrange principlespace debrisboosteradditional fuel tankpulse formulationrelease to atmosphere

Mathematics Subject Classification ID

Application models in control theory (93C95) Orbital mechanics (70M20) Control/observation systems governed by ordinary differential equations (93C15)

Cites Work

• Ballistic aspects of large-size space debris flyby at low Earth near-circular orbits
• On a modification of Newton's methods for the numerical solution of boundary problems

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