STEERING UNIT OF ROCKET Russian patent published in 2017 - IPC F42B10/62 

FIELD: aviation.

SUBSTANCE: rocket control actuator unit consists of an aerodynamic surface, a shaft connected to aerodynamic surface with the ability to rotate, a lever rigidly mounted on the shaft, an actuator pivotally connected to the lever and fixed in the missile body, where the shaft is mounted on rollers in separators and divided shroud, rigidly fixed in the shell of the rocket, and each subsequent roller is located perpendicular to the previous one. Wherein, the rotation mechanism is in the form of a double-row bearing, one row of which, located to the aerodynamic surface, consists of taper rollers placed in separators with thermal gap that meets the requirements for sealing the unit, and the second row, located to the lever, contains needle rollers having axial deflection freedom, 2-3 times greater than the end play of rollers first row. Each row of rollers is filled with a powder mixture of graphite with molybdenum disulphide.

EFFECT: creation of a simple reliable rocket control actuator unit operating at high aerodynamic loads, high ambient temperature, ensuring the requirements for actuator tightness.

1 dwg