ELECTRO-PNEUMATIC CONTROL ACTUATOR OF GUIDED MISSILE Russian patent published in 2000 - IPC

FIELD: flight vehicle control systems. SUBSTANCE: the electro-pneumatic control actuator of guided missile has a body accommodating a relay amplifier and a null machine with a switchgear having a jet tube and a receiver, as well as an electromechanical transducer with an armature and pipe for supply of compressed air to the base of the jet tube. The wall of the jet pipe perpendicular to its axis of rotation has an inlet hole. The outlet section of the jet tube and the inlet ports of the receiver have slots and located in parallel with the axis of rotation of the tube. The pipe for supply of compressed air is installed with a clearance of 0.6 to 0.12 mm opposite the inlet hole of the jet tube. The transducer armature and the jet tube are located in the axis between the supporting bearings. The jet tube may be made thin- walled of plastic. EFFECT: enhanced speed of response of the missile control actuator. 4 cl, 2 dwg