RU2005113080A - METHOD OF DEVELOPING A SPACE VEHICLE ON THE INTERPLANETARY FLIGHT TRAJECTORY - Google Patents

METHOD OF DEVELOPING A SPACE VEHICLE ON THE INTERPLANETARY FLIGHT TRAJECTORY Download PDF

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Publication number
RU2005113080A
RU2005113080A RU2005113080/11A RU2005113080A RU2005113080A RU 2005113080 A RU2005113080 A RU 2005113080A RU 2005113080/11 A RU2005113080/11 A RU 2005113080/11A RU 2005113080 A RU2005113080 A RU 2005113080A RU 2005113080 A RU2005113080 A RU 2005113080A
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RU
Russia
Prior art keywords
earth
developing
space vehicle
flight trajectory
spacecraft
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RU2005113080/11A
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Russian (ru)
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RU2289533C1 (en
Inventor
Геннадий Григорьевич Федотов (RU)
Геннадий Григорьевич Федотов
Original Assignee
Государственное образовательное учреждение высшего профессионального образовани Московский авиационный институт (технический университет) (RU)
Государственное образовательное учреждение высшего профессионального образования Московский авиационный институт (технический университет)
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Priority to RU2005113080/11A priority Critical patent/RU2289533C1/en
Publication of RU2005113080A publication Critical patent/RU2005113080A/en
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Publication of RU2289533C1 publication Critical patent/RU2289533C1/en

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  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Control Of Transmission Device (AREA)

Claims (1)

Способ выведения космического аппарата на межпланетную траекторию полета, включающий его вывод на гелиоцентрическую траекторию, возврат к Земле с приращением скорости и разгон полем тяготения Земли, отличающийся тем, что создают приращение скорости воздействием реактивной силы с помощью маршевых двигателей, обеспечивают возврат аппарата к Земле за расчетное заданное время, обеспечивают равенство угловых движений Земли и космического аппарата относительно Солнца на момент пролета Земли.A method of launching a spacecraft onto an interplanetary flight path, including its introduction to the heliocentric path, returning to the Earth with a speed increment and acceleration by the Earth's gravitational field, characterized in that they create a speed increment by the action of reactive force with the help of marching engines, ensuring the spacecraft returns to the calculated a given time, ensure the equality of the angular movements of the Earth and the spacecraft relative to the Sun at the time of passage of the Earth.
RU2005113080/11A 2005-04-29 2005-04-29 Method of injection of spacecraft into inter-planetary trajectory RU2289533C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2005113080/11A RU2289533C1 (en) 2005-04-29 2005-04-29 Method of injection of spacecraft into inter-planetary trajectory

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Application Number Priority Date Filing Date Title
RU2005113080/11A RU2289533C1 (en) 2005-04-29 2005-04-29 Method of injection of spacecraft into inter-planetary trajectory

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RU2005113080A true RU2005113080A (en) 2006-11-10
RU2289533C1 RU2289533C1 (en) 2006-12-20

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2512067C1 (en) * 2012-12-25 2014-04-10 Александр Вадимович Марков Method of enlarging earth's orbit in solar system
RU2703763C1 (en) * 2018-09-05 2019-10-22 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Method of payload delivery to circumterrestrial orbits by means of space launching vehicle
CN110758775B (en) * 2019-11-21 2021-01-08 北京理工大学 Multi-pulse area hovering method based on asteroid surface observation

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Effective date: 20080430