RU2014112742A - METHOD FOR MANAGING ORIENTATION OF SPACE VEHICLES IN CARRYING OUT EXPERIMENTS WITH SCIENTIFIC EQUIPMENT FOR STUDYING CONVECTION - Google Patents
METHOD FOR MANAGING ORIENTATION OF SPACE VEHICLES IN CARRYING OUT EXPERIMENTS WITH SCIENTIFIC EQUIPMENT FOR STUDYING CONVECTION Download PDFInfo
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- RU2014112742A RU2014112742A RU2014112742/11A RU2014112742A RU2014112742A RU 2014112742 A RU2014112742 A RU 2014112742A RU 2014112742/11 A RU2014112742/11 A RU 2014112742/11A RU 2014112742 A RU2014112742 A RU 2014112742A RU 2014112742 A RU2014112742 A RU 2014112742A
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- spacecraft
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- convection
- orientation
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Abstract
Способ управления ориентацией космического аппарата при проведении экспериментов с научной аппаратурой по изучению конвекции, включающий закрутку космического аппарата, отличающийся тем, что измеряют расстояние от научной аппаратуры до оси закрутки, в процессе закрутки космического аппарата измеряют и фиксируют температуру в научной аппаратуре по изучению конвекции, измеряют угловую скорость космического аппарата, изменяют скорость закрутки космического аппарата на величину, соответствующую изменению измеряемой температуры на, где- среднеквадратическая ошибка измерения температуры, до достижения угловой скоростью величины, определяемой из соотношения, где- модуль микроперегрузки,,- угловая скорость космического аппарата,- радиус-вектор из центра масс космического аппарата до точки установки научной аппаратуры.A method for controlling the orientation of a spacecraft during experiments with scientific equipment for the study of convection, including spinning the spacecraft, characterized in that the distance from the scientific equipment to the spin axis is measured, during the spinning of the spacecraft, the temperature is measured and recorded in scientific equipment for the study of convection, measured the angular velocity of the spacecraft, change the spin speed of the spacecraft by an amount corresponding to a change in the measured temperature by, g e mean square error of temperature measurement, until the angular speed value determined from the relationship somewhere module mikroperegruzki ,, - angular velocity of the spacecraft, - the radius vector from the center of mass of the spacecraft to the point of installation of scientific equipment.
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Application Number | Priority Date | Filing Date | Title |
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RU2014112742/11A RU2581281C2 (en) | 2014-04-01 | 2014-04-01 | Method of spacecraft orientation when conducting experiments with scientific equipment for the study of convection |
Applications Claiming Priority (1)
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RU2014112742/11A RU2581281C2 (en) | 2014-04-01 | 2014-04-01 | Method of spacecraft orientation when conducting experiments with scientific equipment for the study of convection |
Publications (2)
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RU2014112742A true RU2014112742A (en) | 2015-10-10 |
RU2581281C2 RU2581281C2 (en) | 2016-04-20 |
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RU2014112742/11A RU2581281C2 (en) | 2014-04-01 | 2014-04-01 | Method of spacecraft orientation when conducting experiments with scientific equipment for the study of convection |
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RU (1) | RU2581281C2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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RU2691536C1 (en) * | 2018-02-13 | 2019-06-14 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Method of determining three-axis orientation of spacecraft |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5163640A (en) * | 1990-12-14 | 1992-11-17 | Hughes Aircraft Company | Active spin axis control for spinning space vehicles |
US5638303A (en) * | 1995-06-28 | 1997-06-10 | Mcdonnell Douglas Corporation | Non-contacting isolated stabilized microgravity platform system |
RU2128607C1 (en) * | 1995-09-19 | 1999-04-10 | Государственный ракетный центр "КБ. имени академика В.П.Макеева" | Method of three-axis gravitational attitude control of spacecraft in orbit of earth satellite |
US6231011B1 (en) * | 1998-11-02 | 2001-05-15 | University Of Houston System | Satellite angular momentum control system using magnet-superconductor flywheels |
US7159824B2 (en) * | 2003-09-04 | 2007-01-09 | Analex Corporation | Device and method for on-orbit calibration verification of an infrared sensor |
RU2457159C2 (en) * | 2010-08-30 | 2012-07-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Method of uniaxial orientation of elongated space vehicle |
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2014
- 2014-04-01 RU RU2014112742/11A patent/RU2581281C2/en active
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RU2581281C2 (en) | 2016-04-20 |
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