FIELD: rocket engine engineering. SUBSTANCE: after actuating the launching device, combustion products flow through curved hollows 8 and radial passages 7 made in plug 4 and then enter the space of delay charge 5 and ignite it. After a given time interval, when projectile is in a trajectory, ignitor of the cruising engine is actuated by the delay charge and the combustion products of the ignitor ignite the powder charge. EFFECT: enhanced reliability. 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SOLID-PROPELLANT ROCKET ENGINE | 1995 |
|
RU2111372C1 |
| ROCKET ENGINE FOR PROJECTILE | 1992 |
|
RU2024776C1 |
| PROJECTILE | 1995 |
|
RU2103656C1 |
| ROCKET ENGINE OF ROCKET-ASSISTED PROJECTILE | 2016 |
|
RU2620613C1 |
| METHOD OF INCREASING THE DISTANCE OF THE ROCKET-PROPELLED GRENADE | 2017 |
|
RU2647256C1 |
| ROCKET ENGINE FOR ARTILLERY PROJECTILE | 1992 |
|
RU2021544C1 |
| METHOD FOR LAUNCHING OF JET PROJECTILE AND COMPLEX OF FACILITIES REALIZING IT | 2000 |
|
RU2167385C1 |
| SOLID-PROPELLANT ROCKET ENGINE | 2005 |
|
RU2322604C2 |
| METHOD FOR TESTING OF AMMUNITION AND THEIR UNITS | 2008 |
|
RU2388992C2 |
| GUIDED MISSILE SOLID-PROPELLANT ROCKET ENGINE, SOLID PROPELLANT IGNITER AND ROCKET ENGINE NOZZLE ASSEMBLY | 2008 |
|
RU2351788C1 |
