Spacecraft thrust vector control during landing on the moon surface

The problem of optimal control of the thrust vector of a spacecraft power engine, making a decay and soft landing from the circular satellite orbit of the Moon to its surface, is considered. The maximum principle of L.S.Pontryagin was used to determine the control structure. An approach has been developed to determine the optimal thrust control programs for the power engine. The results of the trajectory calculation of a spacecraft landing on the lunar surface are presented. © 2017 Univelt Inc. All rights reserved.

Авторы
Matyushin M.M.1, 2 , Ovechko V.M.1 , Razoumny Y.N. 3 , Skorobogatov O.P.1 , Tyurina D.D.1 , Baranova I.S.1
Издательство
Univelt Inc.
Язык
Английский
Страницы
181-188
Статус
Опубликовано
Том
161
Год
2017
Организации
  • 1 Central Research Institute of Machine, Mission Control Center, 4 Pionerskaya Str, Korolev, 141074, Russian Federation
  • 2 Moscow Aviation Institute, 4, Volokalamskoe Ave, Moscow, 125993, Russian Federation
  • 3 Peoples' Friendship University of Russia (RUDN University), 6 Mikluho- Maklaya Str, Moscow, 117198, Russian Federation
Ключевые слова
Cobalt compounds; Dysprosium compounds; Engines; Lunar landing; Moon; Orbits; Vector control (Electric machinery); Water landing (spacecraft); Control structure; Lunar surface; Optimal controls; Satellite orbit; Spacecraft thrust vector control; Thrust control; Thrust vectors; Trajectory calculations; Sulfur compounds
Дата создания
19.10.2018
Дата изменения
21.04.2021
Постоянная ссылка
https://repository.rudn.ru/ru/records/article/record/6198/
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