RU2008102573A - SPACE VEHICLE CONTROL SYSTEM - Google Patents
SPACE VEHICLE CONTROL SYSTEM Download PDFInfo
- Publication number
- RU2008102573A RU2008102573A RU2008102573/11A RU2008102573A RU2008102573A RU 2008102573 A RU2008102573 A RU 2008102573A RU 2008102573/11 A RU2008102573/11 A RU 2008102573/11A RU 2008102573 A RU2008102573 A RU 2008102573A RU 2008102573 A RU2008102573 A RU 2008102573A
- Authority
- RU
- Russia
- Prior art keywords
- evaporator
- heat exchanger
- input
- coolant
- radiator
- Prior art date
Links
Abstract
Система терморегулирования космического аппарата, включающая в себя контур с двухфазным теплоносителем, содержащий соединенные между собой линиями тракта аккумулятор, гидронасос, теплообменник-испаритель, радиатор-конденсатор, и регулятор температуры пара в теплообменнике-испарителе, отличающаяся тем, что в контур введен установленный на входе в радиатор-конденсатор разделитель жидкой и паровой фаз теплоносителя, вход которого соединен с выходом теплообменника-испарителя, при этом паровой выход разделителя, обеспечивающий подачу паровой фазы теплоносителя, подключен к входу радиатора-конденсатора, а второй выход, обеспечивающий подачу жидкой фазы теплоносителя, - к входу теплообменника-испарителя.The temperature control system of the spacecraft, which includes a circuit with a two-phase coolant, containing an accumulator, a hydraulic pump, a heat exchanger-evaporator, a radiator-condenser, and a steam temperature regulator in the heat exchanger-evaporator, interconnected by path lines, characterized in that the input in the radiator-condenser, a separator of liquid and vapor phases of the coolant, the input of which is connected to the output of the heat exchanger-evaporator, while the steam output of the separator, providing supply rovoy phase coolant, connected to the input capacitor of the radiator, and a second output providing a supply of coolant liquid phase - to the input of the heat exchanger-evaporator.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008102573/11A RU2384491C2 (en) | 2008-01-22 | 2008-01-22 | Spacecraft thermoregulating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008102573/11A RU2384491C2 (en) | 2008-01-22 | 2008-01-22 | Spacecraft thermoregulating system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2008102573A true RU2008102573A (en) | 2009-07-27 |
| RU2384491C2 RU2384491C2 (en) | 2010-03-20 |
Family
ID=41048097
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2008102573/11A RU2384491C2 (en) | 2008-01-22 | 2008-01-22 | Spacecraft thermoregulating system |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2384491C2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2467931C1 (en) * | 2011-04-13 | 2012-11-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Method of thermal control over unit mounted on spaceship and device to this end |
-
2008
- 2008-01-22 RU RU2008102573/11A patent/RU2384491C2/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| RU2384491C2 (en) | 2010-03-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20160123 |