TWO-CHANNEL AIR-DYNAMIC UNIT OF GUIDED MISSILE CONTROL ACTUATOR Russian patent published in 2004 - IPC

FIELD: power control systems of flight vehicles, applicable in control actuators and autopilots of small-sized guided missiles and rockets. SUBSTANCE: the control actuator unit levers, and pneumatic piston engines of the volume type with separate cylinders. The cylinders have a diameter determined from relation d_cyl=0.4D, where D - the diameter of the inner surface of the control actuator unit. The cylinders are located on the side opposite the folding of the controls relative to the transversal plane at angle ϕ relative to the longitudinal plane passing through the axes of rotation of the controls, and on the circumference with diameter d relative to the longitudinal axis of the control actuator unit, determined from relation d=0.6D; ϕ = arcsinK(d_o+h)/0,6D, where d₀ the diameter of the control axle; h - the width of the control axle lever in the joint to the cylinder; K - coefficient taking into account the clearance between the control axle of one channel and the control axle lever of the other channel. EFFECT: enhance power of the control actuator unit. 2 dwg