FIELD: weapons and ammunition.
SUBSTANCE: device for missile launch contains a running launch pipe with front and back end faces, which is connected with the carrier, a gas reflector located at a back end face of the running launch pipe and connected to it. The gas reflector is designed as a circular solid fuel charge with the ignition source located in the circular housing from outer side of the running launch pipe. In the bottom part of the circular housing from the back end face of the running launch pipe a circular row of exhaust outlets is made.
EFFECT: improvement of reliability of work by decrease of power impact of a shock wave on the carrier during start of missile from the launch pipe due to interaction of shock wave with powder flows of gas flowing from the circular housing.
3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ROCKET LAUNCHER | 2015 |
|
RU2577605C1 |
| MISSILE LAUNCHING PLANT | 2013 |
|
RU2519606C1 |
| DEVICE FOR MISSILE LAUNCHING | 2012 |
|
RU2495353C1 |
| ROCKET LAUNCHER | 2015 |
|
RU2577586C1 |
| ROCKET LAUNCHER | 2005 |
|
RU2295689C1 |
| MISSILE LAUNCHING PLANT | 2014 |
|
RU2545155C1 |
| DEVICE FOR ROCKET LAUNCHING | 2004 |
|
RU2275578C1 |
| MISSILE LAUNCHER | 2006 |
|
RU2318172C1 |
| ROCKET LAUNCHER | 2007 |
|
RU2345309C1 |
| METHOD FOR REDUCING GAS-DYNAMIC INFLUENCE ON GROUND OF START POSITION AND LAUNCHING STATION OF STARTING MISSILE JET STREAM AT ANGLES CLOSE TO VERTICAL ANGLE AND DEVICE FOR ITS IMPLEMENTATION | 2012 |
|
RU2481540C1 |
