RU2009116790A - METHOD FOR RELEASING ADDITIONAL USEFUL LOAD AND SPACE DEVICE OF FLEXIBLE ASSEMBLY FOR ITS IMPLEMENTATION - Google Patents
METHOD FOR RELEASING ADDITIONAL USEFUL LOAD AND SPACE DEVICE OF FLEXIBLE ASSEMBLY FOR ITS IMPLEMENTATION Download PDFInfo
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- RU2009116790A RU2009116790A RU2009116790/11A RU2009116790A RU2009116790A RU 2009116790 A RU2009116790 A RU 2009116790A RU 2009116790/11 A RU2009116790/11 A RU 2009116790/11A RU 2009116790 A RU2009116790 A RU 2009116790A RU 2009116790 A RU2009116790 A RU 2009116790A
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- spacecraft
- payload
- additional
- main
- transport position
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- 238000000034 method Methods 0.000 title claims abstract 5
- 241000238367 Mya arenaria Species 0.000 claims abstract 2
- 238000010790 dilution Methods 0.000 claims abstract 2
- 239000012895 dilution Substances 0.000 claims abstract 2
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Abstract
1. Способ выведения полезной нагрузки, включающий хотя бы один основной космический аппарат и дополнительный космический аппарат со служебными бортовыми системами и отсеком полезного груза, отличающийся тем, что массу дополнительного космического аппарата с полезным грузом в гибкой оболочке выбирают исходя из максимальной загрузки ракеты-носителя и размещают с основным космическим аппаратом в остаточном объеме головного обтекателя, а после выведения на орбиту отделяют дополнительный космический аппарат, переводят его в транспортное положение и доставляют в заданную точку космического пространства, используя собственные двигатели, после чего стыкуют для использования полезного груза или его складирования. ! 2. Устройство для реализации способа по п.1 в виде дополнительного космического аппарата, снабженного служебными системами и отсеком полезного груза, отличающееся тем, что служебные системы выполнены в виде отдельных минимизированных блоков, связанных между собой гибкими электрическими и трубопроводными коммуникациями, длиной, определяемой из удобства их размещения около основного космического аппарата, а контейнер полезного груза выполнен в мягкой оболочке, снабжен разъемом расхода или перелива полезного груза, причем дополнительный космический аппарат имеет технологические элементы крепления к основному космическому аппарату, снабжен системой перевода дополнительного космического аппарата в транспортное положение, которая содержит надувные шланги оболочки полезного груза и электрореактивные двигатели разведения и закрутки блоков дополнительного космического аппарата между собой 1. The method of launching the payload, including at least one main spacecraft and an additional spacecraft with onboard flight systems and a payload compartment, characterized in that the mass of the additional spacecraft with payload in a flexible shell is selected based on the maximum load of the launch vehicle and placed with the main spacecraft in the residual volume of the head fairing, and after putting into orbit, an additional spacecraft is separated, transferred to the transport position and delivered to a given point in outer space using their own engines, and then joined to use the payload or its storage. ! 2. The device for implementing the method according to claim 1 in the form of an additional spacecraft equipped with service systems and a payload compartment, characterized in that the service systems are made in the form of separate minimized units interconnected by flexible electrical and pipelines, the length determined from the convenience of their placement near the main spacecraft, and the payload container is made in a soft shell, equipped with a flow or payload overflow connector, with additional spacecraft has technological elements attached to the main spacecraft, the transfer system is provided with additional spacecraft to the transport position, which comprises inflatable hoses payload envelope and electric rocket engines dilution and spin spacecraft additional units together
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2009116790/11A RU2420431C2 (en) | 2009-05-05 | 2009-05-05 | Spacecraft of flexible configuration for extra payload |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2009116790/11A RU2420431C2 (en) | 2009-05-05 | 2009-05-05 | Spacecraft of flexible configuration for extra payload |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2009116790A true RU2009116790A (en) | 2010-11-10 |
| RU2420431C2 RU2420431C2 (en) | 2011-06-10 |
Family
ID=44025739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2009116790/11A RU2420431C2 (en) | 2009-05-05 | 2009-05-05 | Spacecraft of flexible configuration for extra payload |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2420431C2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2561888C2 (en) * | 2013-12-05 | 2015-09-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Space convertible module |
| RU2581274C2 (en) * | 2014-04-29 | 2016-04-20 | Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Modular spacecraft |
| RU2572277C2 (en) * | 2014-05-20 | 2016-01-10 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Spacecraft with extra payload |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3330510A (en) * | 1967-01-19 | 1967-07-11 | Caldwell C Johnson | Orbital escape device |
| JP2520250B2 (en) * | 1987-03-16 | 1996-07-31 | 竹内 康人 | Protected structures in outer space |
| FR2649667B1 (en) * | 1989-07-17 | 1991-09-20 | Centre Nat Etd Spatiales | METHOD FOR LAUNCHING IN THE SPACE OF A CAPSULE AND CORRESPONDING LAUNCHING MEANS |
| RU2241644C1 (en) * | 2003-04-04 | 2004-12-10 | Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт машиностроения" | Inflatable independent space module |
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2009
- 2009-05-05 RU RU2009116790/11A patent/RU2420431C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2420431C2 (en) | 2011-06-10 |
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