FIELD: armament.
SUBSTANCE: the guided missile has a body, frame with folding aerodynamic control surfaces hinge-installed in the drive shaft trunnions, deployment and fixation mechanism of the aerodynamic control surfaces with retaining springs and a pyrotechnical cartridge sealed with a membrane, the pyrotechnical cartridge is installed in a shaft rigidly coupled by pins to the drive shafts and having ducts communicating the pyrotechnical cartridge chamber with the working spaces of the pistons installed in the central holes of the drive shafts. The ducts in the shaft are made on the opposite sides of the pins. The duct inlets are located above the surface of the bottom wall of the pyrotechnical cartridge chamber at a height exceeding the thickness of the pyrotechnical cartridge membrane. The retaining springs are located in the end face piston undercuts made on the side of the shaft.
EFFECT: enhanced reliability of the control surface deployment mechanism.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GUIDED PROJECTILE | 2001 |
|
RU2196295C1 |
| CONTROLLED PROJECTILE, STEERING DRIVE GROUP OF CONTROLLED PROJECTILE, PNEUMATIC DISTRIBUTION DEVICE OF STEERING DRIVE OF CONTROLLED PROJECTILE, MECHANISM OF INITIATION OF STEERING DRIVE OF CONTROLLED PROJECTILE | 2017 |
|
RU2669979C1 |
| METHOD FOR CONTROL OF SPIN-STABILIZED MISSILE AND GUIDED MISSILE | 2004 |
|
RU2275584C2 |
| METHOD FOR CONTROL OF SPIN-STABILIZED MISSILE AND GUIDED MISSILE | 2000 |
|
RU2166727C1 |
| GUIDED MISSILE AND SERVO UNIT FOR IT | 2000 |
|
RU2184927C1 |
| GUIDED MISSILE | 2003 |
|
RU2244897C1 |
| METHOD OF OPENING CONTROL SURFACES OF GUIDED PROJECTILE ACTUATOR UNIT AND ACTUATOR UNIT FOR REALIZATION OF THIS METHOD | 2002 |
|
RU2237598C2 |
| UNIVERSAL ARTILLERY COMPLEX FOR TELESCOPIC CARTRIDGE | 2018 |
|
RU2696949C2 |
| MISSILE WITH NORMAL AERODYNAMIC CONFIGURATION | 2003 |
|
RU2239780C1 |
| FOLDING AERODYNAMIC CONTROL | 2005 |
|
RU2284450C1 |
