FIELD: engines and pumps.
SUBSTANCE: electro-thermal rocket engine (1) heating compartment (20) for fluid working medium (4) to pass there through before being ejected from nozzle (8). Working medium is heated by either ohmic or electric-arc method. Note also that spacecraft comprises electric power source (22) incorporating photo galvanic elements (24) fitted on heat exchanger (10). Working fluid (4) passes through heat exchanger upstream of aforesaid heating unit (20). Electric power source (22) comprises concentrator (28) directing sun light onto photo galvanic elements (24). Heat generated on the latter is transferred to working medium (4).
EFFECT: higher efficiency of spacecraft power plant.
7 cl, 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SOLAR HEAT ROCKET ENGINE AND METHOD OF ITS OPERATION | 2002 |
|
RU2197630C1 |
| SOLAR THERMAL ROCKET ENGINE | 1998 |
|
RU2126493C1 |
| SPACE-BASED POWER SYSTEM | 2009 |
|
RU2587209C9 |
| METHOD OF OPTICAL PROCESSING DEVICE UNUSED OPTICAL RADIATION ENERGY RECOVERY, RECOVERY DEVICE AND OPTICAL PROCESSING DEVICE | 2013 |
|
RU2611608C2 |
| HEAT ROCKET ENGINE | 1998 |
|
RU2194184C2 |
| SPACECRAFT PROPULSION SYSTEM AND METHOD | 2015 |
|
RU2684968C2 |
| LIQUID-PROPELLANT ROCKET ENGINE OF MULTIPLE START-UP (VERSIONS) | 2008 |
|
RU2364742C1 |
| SOLAR GENERATOR AND METHOD OF SOLAR RADIATION CONVERSION INTO ELECTRICITY | 2017 |
|
RU2662244C1 |
| LOW-THRUST LIQUID-PROPELLANT ROCKET ENGINE | 2001 |
|
RU2204047C2 |
| LIQUID-PROPELLANT THRUSTER | 1999 |
|
RU2176748C2 |
