Inductive counteractive momentum sphere system

Abstract

An inductive counteractive momentum sphere system comprises a counteractive momentum sphere module, a displacement detection and drive circuit, a revolving speed detection module and a control system. The counteractive momentum sphere module is composed of a spherical rotor (1) and a coil electrode cage (2) arranged around the spherical rotor (1). The spherical rotor (1) conducts suspension driving and rotation driving through an alternating magnetic field generated by the coil electrode cage (2). The revolving speed detection module comprises a revolving speed detection probe (3) and a revolving speed detection circuit and detects out the revolving speed of the spherical rotor (1). A displacement detection part in the displacement detection and drive circuit detects out relative displacement of the spherical rotor (1). The control system generates control signals according to collected revolving speed information and displacement information of the spherical rotor (1), and a drive part in the displacement detection and drive circuit controls the current of the coil electrode cage (2) to change the alternating magnetic field so as to achieve feedback control over the spherical rotor (1).

Description

technical field [0001] The invention relates to a reaction momentum ball system used for satellite attitude adjustment. Background technique [0002] At present, the reaction flywheel momentum exchange system is the main method of spacecraft attitude control, especially the three-axis precise attitude control of spacecraft. However, in order to complete the three-axis attitude control of the spacecraft, at least three sets of flywheels are required to be installed in an orthogonal manner. On this basis, if you want to increase redundancy, you need to use more flywheels, which will bring about the quality of the system. , power consumption and efficiency limitations. In addition, frequent momentum exchange needs to occur between the flywheels of each shaft. Due to the friction between the shaft and the bearing, the control accuracy and life of the system are greatly limited. [0003] The publication number is WO2010117819A1, and the patent titled Reaction sphere for spacecr...

AI Technical Summary

Problems solved by technology

However, the icosahedral electrode arrangement adopted in this invention requires a relatively complicated calculation process when implementing the control of momentum exchange, which takes up relatively large computing resources, which is not conducive to the timeliness requirements of spacecraft attitude control.

At the same time, the spherical rotor of the reaction ball is made of a single copper material, which is easily oxidized and affects the conductivity, making the induced current weak and the driving efficiency low

In addition, in order to monitor the displacement and rotational speed of the spherical rotor, additional displacement sensors and rotational speed sensors are required, which significantly increases the volume, mass and power consumption of the system, reduces the functional density ratio, and is not conducive to use on microsatellites

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