FIELD: astronautics.
SUBSTANCE: invention relates to space engineering and may be used to provide power to spacecraft (SC) and stations. Power supply system is intended for use on spacecraft and stations in a space environment. In present invention into existing fluid temperature control system comprising a housing within which is located cooling circuit and heating, consisting of series-connected heat exchanger to reservoir coolant, having a control valve, radiator etching valve magneto-hydrodynamic pump for circulating coolant in kennel, after heat exchanger is introduced turbine connected to an electric generator, via a control system which is connected to battery and load.
EFFECT: use of thermal control system for obtaining additional energy.
1 cl, 1 dwg
Title | Year | Author | Number |
---|---|---|---|
SPACECRAFT ENDOTHERMAL CONTROL SYSTEM | 2011 |
|
RU2463222C1 |
SPACECRAFT | 2020 |
|
RU2749928C1 |
SPACECRAFT | 1998 |
|
RU2144889C1 |
SPACECRAFT | 2001 |
|
RU2198830C2 |
EARTH REMOTE SOUNDING SPACECRAFT | 2012 |
|
RU2493056C1 |
SPACECRAFT | 2013 |
|
RU2543433C2 |
SPACECRAFT | 2000 |
|
RU2196079C2 |
SPACECRAFT | 1999 |
|
RU2164881C1 |
SELF-CONTAINED POWER AND HEAT SUPPLY SYSTEM OF ROOMS IN DWELLING HOUSES AND INDUSTRIAL AREAS | 2003 |
|
RU2249125C1 |
METHOD OF OPERATION OF THE LITHIUM-ION ACCUMULATOR BATTERY IN THE COMPOSITION OF A SPACE APPARATUS FOR NON-TIGHT EXECUTION | 2016 |
|
RU2625173C1 |
Authors
Dates
2016-05-20—Published
2015-04-30—Filed