FIELD: defence equipment. SUBSTANCE: in the middle part the axles of the control surfaces are connected by a double-arm lever. One arm of the lever is linked with the control actuator movable parts, and the other is made as a counterweight. The product of the masses of the control actuator movable parts and kinematic members by the lever arm is related to the product of the mass of the counterweight by its arm as 1:(0.8-1.2). EFFECT: enhanced reliability of functioning and provision of high dynamic characteristics at an action of considerable axial g-loads caused by operation of the propulsion system on the boost trajectory of missile flight. 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GUIDED MISSILE ACTUATOR ASSEMBLY | 1996 |
|
RU2101667C1 |
| GUIDE PROJECTILE | 1996 |
|
RU2096735C1 |
| GUIDED MISSILE ACTUATOR ASSEMBLY | 1996 |
|
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| GUIDED MISSILE AND SERVO UNIT FOR IT | 2000 |
|
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| METHOD FOR CONTROL OF SPIN-STABILIZED MISSILE AND GUIDED MISSILE | 2000 |
|
RU2166727C1 |
| METHOD OF CHECK-UP OF BRINGING TO SERVICEABLE CONDITION OF SEALED AUTOPILOT UNIT | 1997 |
|
RU2126949C1 |
| GUIDED MISSILE CONTROL ACTUATOR UNIT | 1994 |
|
RU2066834C1 |
| BLOCK OF STEERING DRIVE OF GUIDED MISSILE | 1997 |
|
RU2121649C1 |
| GUIDED MISSILE | 1998 |
|
RU2135946C1 |
| METHOD OF OPENING CONTROL SURFACES OF GUIDED PROJECTILE ACTUATOR UNIT AND ACTUATOR UNIT FOR REALIZATION OF THIS METHOD | 2002 |
|
RU2237598C2 |
