| 摘要 |
power control systems of flight vehicles, most expediently applicable in control bays of small-sized guided missiles with a homing head fired from the barrel of a tank gun, artillery guns, etc. SUBSTANCE: placed in succession in the guided missile control bay in the direction of action of starting - g-load are the homing head, electronic unit, control actuator and the electric power unit, the control actuator is rigidly secured on the electric power in a spaced relation to the body of the autopilot unit. EFFECT: enhanced safety factor and reliability of operation of the control bay of the guided missile with a homing head at an action of starting g-load of a high intensity at the instant of a shot from an artillery gun. 4 cl, 3 dwg
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