FIELD: weapons and ammunition.
SUBSTANCE: missile part with stabiliser of rocket projectile comprises a housing with the multinozzle unit and a foldout stabiliser with blades. The blades are mounted at a zero angle to the longitudinal axis of the housing. The stabiliser blades are made flat and have an asymmetrical tapering of chamfered front edges. The chamfer is located on the surface of the blade facing in the direction opposite to the rotation of the missile part. The angle of tapering in a plane perpendicular to the front edges is located within β=10°-30°.
EFFECT: increase reliability of functioning of the missile part.
3 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ROCKET MISSILE | 2006 |
|
RU2343397C2 |
| SUPERSONIC SPIN-STABILIZED MISSILE | 2023 |
|
RU2809446C1 |
| MISSILE | 2023 |
|
RU2814640C1 |
| ROCKET SECTION WITH STABILISING DEVICE OF PROJECTILE | 2015 |
|
RU2581097C1 |
| MISSILE WITH AIR-JET ENGINE | 2015 |
|
RU2585211C1 |
| ROTATING ROCKET PROJECTILE LAUNCHED FROM A TUBULAR GUIDE | 2022 |
|
RU2795731C1 |
| SPIN-STABILIZED SUPERSONIC MISSILE | 2000 |
|
RU2166178C1 |
| SUPERSONIC CONTROLLED PROJECTILE | 2011 |
|
RU2459177C1 |
| MISSILE STABILIZER | 2023 |
|
RU2814624C1 |
| ROTATING PROJECTILE LAUNCHED FROM A SMOOTHBORE TUBULAR RAIL | 2021 |
|
RU2773057C1 |
