FIELD: armament.
SUBSTANCE: the guided missile has a leading shaped charge, warhead, control actuator unit positioned between them, fairing with an air-intake. A base is installed in the nose compartment, with the controls deployment mechanism positioned on it. Grooves for outlet of the controls are made in the fairing. The area of the grooves in the fairing being the releasing ducts is made in relationship of 10-15 of the air-intake duct area.
EFFECT: enhanced efficiency of air release from the release manifold through the fairing grooves.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GUIDED MISSILE | 2003 |
|
RU2257533C1 |
| GUIDED MISSILE NOSE CONE | 1995 |
|
RU2089834C1 |
| GUIDED MISSILE NOSE CONE | 1996 |
|
RU2100767C1 |
| ROCKET | 2001 |
|
RU2191983C1 |
| GUIDED MISSILE | 1994 |
|
RU2084809C1 |
| GUIDED MISSILE | 2008 |
|
RU2370725C1 |
| METHOD OF TARGET DESTRUCTION BY PREDOMINANTLY GUIDED MISSILE AND MISSILE FOR ITS IMPLEMENTATION | 2002 |
|
RU2197708C1 |
| GUIDED MISSILE | 2007 |
|
RU2351886C1 |
| GUIDED SHELL LAUNCH METHOD AND THE GUIDED SHELL | 2006 |
|
RU2324142C2 |
| GUIDED MISSILE | 2008 |
|
RU2370726C1 |
