Device and method for realizing sun capture by zero momentums of micro-satellites

Abstract

The invention provides a device and a method for realizing sun capture by zero momentums of micro-satellites. The device comprises an analog sun sensor, a magnetometer and a magnetic torquer, whereinthe analog sun sensor and the magnetometer are used for together determining the attitude of a satellite; and the magnetic torquer is used for providing a control moment in a rate damping process andused for enabling a normal axis of a solar array of the satellite to point to the vector direction of the sun as well as controlling an included angle between a normal line of the solar array of the satellite and the vector direction of the sun to be less than a preset threshold, thereby realizing sun capture by a zero momentum magnetic control mode of the satellite. The device and the method provided by the invention simplify the working mode of an attitude and orbit control system and improve the working reliability when the satellite enters an orbit in the early stage.

Description

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AI Technical Summary

Benefits of technology

This technology described in this patented describes a small spacecraft used during launch orbits where it's difficult to track its position accurately due to lack of any external forces like gravity. However, there may still exist some other factors affecting how well these satellites work properly: they have no angular velocity (angular rotation) at their original start time; they use very little battery power when navigating through gaps between them and around obstacles while moving about without losing altitude accuracy. They rely heavily upon accurate navigation signals obtained from GPS systems which require high computational capabilities. Additionally, current methods involve complex calculations involving multiple components - including various sensors and actuators - making them expensive and prone to failure over long periods of usage.

Problems solved by technology

The technical problem addressed during this patented process for achieving quicker reentry from space orbit into low earth orbits (LEO) involves controlling the orientation angle of an object's axis when it moves towards its destination without adding too many components that increase their mass and size. This makes launches more difficult due to increased vibrations caused by gravity waves.

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