Spacecraft reaction fluid actuator ring

The present invention provides a fluid loop reaction spacecraft actuator, comprising: a mounting base for mounting the fluid and the corresponding ring means; fluid loop, for generating angular momentum; solenoid pump assembly, mainly a permanent magnet or an electromagnet and electrode plates etc., the drive ring within the fluid flow of the liquid at a controlled rate; fill fluid, using a conductive liquid material means within the fluid ring pump flows under the electromagnetic drive assembly; shield case, the electromagnetic pump outside the cover for electric and magnetic shielding to prevent interference of external devices. The present invention utilizes an electromagnetic driving the liquid ring pump to generate angular momentum to achieve the attitude control of the spacecraft can provide a multi-axis controlled spacecraft moment especially micro satellites attitude control, and no mechanical rotary bearing member, having high reliability, simple structure small power consumption characteristics.