FIELD: astronautics.
SUBSTANCE: invention can be used for launching missiles from flow-through launch tubes. Rocket launcher comprises a launching flow pipe connected with carrier with bottom edge and installed on the carrier jet controls reduction of gas-dynamic influence on carrier at start. Outputs of the jet controls reduction of gas-dynamic influence on carrier at start are composed of radial lengthwise slots arranged behind bottom edge starting flow pipe.
EFFECT: technical result is increased reliability of operation by reducing shock wave effects on carrier at missile launching.
1 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| MISSILE LAUNCHING PLANT | 2013 |
|
RU2519606C1 |
| MISSILE LAUNCHING PLANT | 2014 |
|
RU2545154C1 |
| ROCKET LAUNCHER | 2015 |
|
RU2577586C1 |
| DEVICE FOR MISSILE LAUNCHING | 2012 |
|
RU2495353C1 |
| DEVICE FOR ROCKET LAUNCHING | 2004 |
|
RU2275578C1 |
| ROCKET LAUNCHER | 2008 |
|
RU2371657C1 |
| ROCKET LAUNCHER | 2005 |
|
RU2295689C1 |
| MISSILE LAUNCHING PLANT | 2014 |
|
RU2545155C1 |
| 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 |
| ROCKET LAUNCHER | 2009 |
|
RU2395053C1 |
