A Spacecraft Fluid Ring Reaction Actuator

Abstract

The invention provides a spacecraft fluid ring reaction performing mechanism. The spacecraft fluid ring reaction performing mechanism comprises a mounting base used for mounting a fluid ring and corresponding devices, the fluid ring used for generating angular momentum, an electromagnetic pump assembly which mainly comprises a permanent magnet or an electromagnet and an electrode board pair and is used for driving liquid in the fluid ring to do controllable-speed flowing, a filling liquid which employs a conductive liquid material, is mounted in the fluid ring and flows under the driving action of the electromagnetic pump assembly, and a shielding box which covers outside an electromagnetic pump and is used for shielding an electric field and a magnetic field to prevent interference of external devices. The spacecraft fluid ring reaction performing mechanism utilizes the electromagnetic pump to drive the liquid ring to generate angular momentum to realize attitude control of a spacecraft, can provide multi-axial control moments for attitude control of spacecrafts especially micro satellites, requires no mechanical rotation bearing part and further has properties of high reliability, simple structure and small energy consumption.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude control, in particular to a spacecraft fluid ring reaction actuator used in a spacecraft attitude control system. Background technique [0002] The attitude control actuator is a device that generates control torque and changes the attitude motion of the spacecraft according to the control instructions given by the attitude controller of the spacecraft. At present, the actuators that can be used for active attitude control of spacecraft mainly include thrusters, momentum wheels or reaction wheels, etc. Thrusters generate control torque by discharging a certain mass of gas to achieve spacecraft attitude control, but the spacecraft itself has limited fuel, and the inherent instantaneous effect of thrusters will cause vibration of flexible accessories and affect the control accuracy of the spacecraft. The momentum wheel or the reaction wheel exchanges the angular momentum with the spacec...

AI Technical Summary

Problems solved by technology

Thrusters generate control torque by discharging a certain mass of gas to achieve spacecraft attitude control, but the spacecraft itself has limited fuel, and the inherent instantaneous effect of the thruster will cause vibration of the flexible attachment, affecting the control accuracy of the spacecraft

The momentum wheel or the reaction wheel exchanges the angular momentum with the spacecraft through the high-speed flywheel rotation to realize the attitude control of the spacecraft, but its structure is complex, the volume and weight are large, and the non-uniformity of the moving parts under high-speed rotation will produce high frequency Interference, prone to wear, limited reliability and lifetime

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