FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises housing made of composite with front and rear bottoms interconnected by cylindrical section, solid-propellant charge secured to housing and recessed nozzle. Reusable blank flange is mounted at front bottom with igniter arranged at outer side. Charge outer radius, charge channel radius, nozzle throat radius and housing structural shell cylindrical section thickness are defined by ratios protected by propose invention.
EFFECT: possibility to define specific thrust pulse and solid-propellant combustion rate at strained state.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| MODEL ENGINE FOR DETERMINING BURNING RATE OF SOLID PROPELLANT IN STRESSED-DEFORMED STATE | 2002 |
|
RU2201520C1 |
| SIMULATOR OF SOLID-PROPELLANT ROCKET ENGINE FOR INITIAL PHASE OF OPERATION | 2005 |
|
RU2273753C1 |
| METHOD OF PRESSURE GASDYNAMIC STABILISATION IN PILOT ENGINE CHAMBER WITH SOLID-PROPELLANT CHARGES WITH HIGH COMBUSTION RATE SUSCEPTIBILITY TO PRESSURE | 2006 |
|
RU2327052C2 |
| INSTALLATION FOR DETERMINATION OF BURNING RATE OF SOLID PROPELLANT IN STRESSED- DEFORMED STATE | 2001 |
|
RU2188963C1 |
| SOLID-PROPELLANT ROCKET ENGINE | 2005 |
|
RU2305790C1 |
| METHOD OF ROCKET ENGINE SOLID FUEL UTILISATION | 2007 |
|
RU2345283C1 |
| MOCKUP ENGINE FOR DETERMINING BURNING RATE OF ROCKET SOLID PROPELLANT | 2002 |
|
RU2215170C1 |
| SOLID-PROPELLANT CHARGE | 2001 |
|
RU2196916C1 |
| COMPOSITE SOLID-PROPELLANT ROCKET ENGINE | 2002 |
|
RU2211351C1 |
| SOLID-PROPELLANT ROCKET | 2012 |
|
RU2497007C1 |
