FIELD: torpedo armament. SUBSTANCE: the torpedo has a body with rudders and a rudder drive including a distributing device and an actuator engine, the rudder drive is positioned in the rudder made in the form of a fixed hydrofoil with a rotary vane. The actuator engine is made in the form of a rocker installed in the cavity formed in the hydrofoil and divided by the rocker axle into working chambers communicating by the outlet ducts with the environment through the slits in the rear edge of the hydrofoil, and by the inlet ducts - with the slit-like receiving ports of the electromagnetic distributing device. The distributing device consists of cores E-shaped in section with windings secured in the hydrofoil and positioned one opposite the other, and a rotary armature located between the cores. One end of the armature is secured on the torsion bar in the hydrofoil, and the opposite one is installed before the receiving ports for their alternative closing. The cavity formed between the cores communicates with the environment through water scoops made in the ledges of the hydrofoil profile. The rudder vane is kinematically linked with the actuator engine by a flexible tie enveloping the axles of the rocker and rudder vane and secured on these axles. EFFECT: improved dimensional characteristics of the torpedo due to use of water inflowing energy for displacement of rudders in torpedo motion. 3 dwg
Title | Year | Author | Number |
---|---|---|---|
AIR-DYNAMIC CONTROL ACTUATOR | 2000 |
|
RU2167386C1 |
AFTERBODY SECTION OF AIR-DYNAMIC STEERING GEARS FOR CONTROLLED AIRCRAFTS (PREFERABLY FOR CONTROLLED AERIAL BOMBS) AND AIR ACTUATOR OF STEERING GEAR | 2009 |
|
RU2418261C2 |
ELECTRO-PNEUMATIC CONTROL ACTUATOR OF GUIDED MISSILE | 1999 |
|
RU2157503C1 |
INTERRUPTED PNEUMATIC ACTUATOR OF CONTROL SYSTEM OF SPIN-STABILIZED MISSILES AND METHOD FOR MONITORING OF ITS DYNAMICS | 2000 |
|
RU2184340C2 |
ELECTROPNEUMATIC VALVE | 2001 |
|
RU2205312C2 |
METHOD FOR CONTROL OF MISSILE AND CONTROL ACTUATOR POD (MODIFICATIONS) | 2005 |
|
RU2288439C1 |
GUIDED MISSILE AND SERVO UNIT FOR IT | 2000 |
|
RU2184927C1 |
ELECTROMAGNETIC UNIT OF GUIDED MISSILE CONTROL ACTUATOR | 2005 |
|
RU2283472C1 |
AIR-DYNAMIC UNIT OF GUIDED MISSILE CONTROL ACTUATOR | 2000 |
|
RU2172927C1 |
METHOD OF AND PNEUMATIC CONTROL ACTUATOR TO CONTROL GUIDE MISSILE | 2003 |
|
RU2254501C2 |
Authors
Dates
2002-09-10—Published
2000-08-21—Filed