FIELD: motors and pumps.
SUBSTANCE: hybrid rocket engine comprises a combustion chamber with a charge of solid fuel arranged in it with an internal through channel, and a nozzle block. In the input section of the charge a nozzle is placed for oxidiser supply to the charge channel. The charge of solid fuel comprises combustible and oxidising components, and the mass content of the oxidising component in the charge is increased monotonically along its length in the direction of the nozzle unit in accordance with an equation comprising the characteristics of the charge and the fuel components of the hybrid rocket engine.
EFFECT: invention enables to improve specific impulse of engine thrust.
4 dwg, 8 tbl
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD FOR DETERMINING COMBUSTION RATE OF SOLID FUEL IN GAS STREAM | 2020 |
|
RU2749473C1 |
| METHOD OF INCREASING HYBRID ROCKET ENGINE THRUST | 2015 |
|
RU2598984C2 |
| FUEL COMPOSITION (OPTIONS) | 2017 |
|
RU2649573C1 |
| METHOD TO CONTROL RATIO OF PROPELLANT COMPONENTS IN HYBRID PROPELLANT ROCKET ENGINE | 2004 |
|
RU2274761C2 |
| METHOD OF PRODUCING MIXED SOLID FUEL | 2008 |
|
RU2429282C2 |
| HYBRID ROCKET ENGINE | 2012 |
|
RU2511986C2 |
| HYBRID ROCKET ENGINE | 2007 |
|
RU2359145C1 |
| METHOD OF CONTROLLING RATE OF COMBUSTION OF MIXED SOLID FUEL | 2008 |
|
RU2423338C2 |
| SMALL-PULSE IMPULSE RPRE WORKING IN THE LOW-SPEED DETONATION MODE | 2016 |
|
RU2644804C1 |
| NOVEL PROPELLANTS BASED ON METAL PERCHLORATES | 2014 |
|
RU2594218C2 |
