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Optimal elliptic maneuvering of a spacecraft with a solar engine

The analysis of the optimal controls ensuring the minimization of the con-sumption of the working fluid of an electric propulsion (EP) of a space-craft that makes a flight between close elliptical orbits is provided. Whenmodeling the thrust of the EP, features of its generation in the plasmaEPs and...

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Datum:2017
Автори та афіліації:
  • Б. М. Кiфоренко — Iнститут механiки iм. С.П.Тимошенка НАН України
  • Я. В. Ткаченко — Iнститут механiки iм. С.П.Тимошенка НАН України
  • І. Ю. Васильєв — Київський нацiональний унiверситет iменi Тараса Шевченка
Ключові слова:keywords
Hauptverfasser: Kiforenko, B. M., Ткаченко, Я. В., Васильєв, І. Ю., Кiфоренко, Б. М.
Format: Artikel
Sprache:Ukrainisch
Veröffentlicht: Інститут математики НАН України 2017
Online Zugang:https://trim.imath.kiev.ua/index.php/trim/article/view/329
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Назва журналу:Transactions of Institute of Mathematics of NAS of Ukraine
Завантажити файл: Pdf

Institution

Transactions of Institute of Mathematics of NAS of Ukraine
Beschreibung
Zusammenfassung:The analysis of the optimal controls ensuring the minimization of the con-sumption of the working fluid of an electric propulsion (EP) of a space-craft that makes a flight between close elliptical orbits is provided. Whenmodeling the thrust of the EP, features of its generation in the plasmaEPs and the volt-ampere characteristics of a solar battery are accountedfor. In illustrative examples, the shadow effect on the efficiency of the EPoperation was studied. It is shown that there are such relations of locationand duration of the shadow arcs of the transfer trajectory, in which theshadow does not affect the quality of the optimal maneuver performance.

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