FIELD: armament.
SUBSTANCE: the missile banking in a container made of a composite material has a rocket engine with a stabilizer unit. The missile is provided with rollers uniformly distributed in the circumference length and installed on its body by means of axles. The rollers are fastened at an equal angle relative to the missile longitudinal axis in the direction of its banking for engagement with the container inner surface by its teeth with an acute angle at the vertex made on the lateral surface of the rollers at an angle relative to their ends in the direction of missile banking.
EFFECT: provided required rate of roll of the missile at its exit from the container.
5 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| MISSILE IN TRANSPORTER-LAUNCHER CONTAINER | 2006 |
|
RU2331838C1 |
| METHOD FOR LAUNCHING OF TWO-STAGE GUIDED MISSILE FROM AIR CARRIER | 2006 |
|
RU2321825C2 |
| GUIDED MISSILE | 1995 |
|
RU2103655C1 |
| AIR MISSILE SYSTEM WITH AN UNMANNED PERCUSSIVE AIRCRAFT HELICOPTER | 2018 |
|
RU2710317C1 |
| SHUTTLECRAFT | 2012 |
|
RU2495799C1 |
| ROCKET ENGINE NOZZLE DESIGNED FOR ROTATING ROCKET RELATIVE TO LONGITUDINAL AXIS | 2001 |
|
RU2211939C2 |
| GUIDED MISSILE | 2005 |
|
RU2272240C1 |
| SPIN-STABILIZED MISSILE | 2003 |
|
RU2241953C1 |
| MISSILE TAKE-OFF AND ORIENTATION ACTUATING SYSTEM | 1995 |
|
RU2082946C1 |
| GYRATING ROCKET STAGE WITH COMBINED POWER PLANT AND METHOD OF CONTROLLING ROCKET FLIGHT | 2010 |
|
RU2427507C1 |
