Cubesat bias momentum attitude control system

Abstract

The invention discloses a cubesat bias momentum attitude control system. The cubesat bias momentum attitude control system comprises a mounting frame, a base, a control module and a measuring and control component; the base is fixed at the bottom of the mounting frame; the control module is fixed at the upper part of the base and positioned in the mounting frame; the measuring and control component comprises two bias momentum wheels, four sun sensors, a three-axis magnetic torquer, a gyroscope, a GPS receiver and two paths of magnetometers; the two bias momentum wheels are fixed in the mounting frame; the four sun sensors are correspondingly fixed at four external side edges of the mounting frame; the gyroscope is fixed in the base; and the GPS receiver and the two-way magnetometer are integrated on the control module. The cubesat bias momentum attitude control system has the advantages that the volume is small; the functional density is high; by reserving four-corner through holes, the system can be fixed in a cubesat through studs; the system is suitable for design standards of an existing cubesat; and moreover, the mounting space for the two bias momentum wheels is reserved in the system; and as the two paths of magnetometers are integrated in a control circuit board, the reliability of the attitude control system can be effectively enhanced.

Description

technical field [0001] The invention relates to the technical field of cube stars, in particular to a cube star bias momentum attitude control system. Background technique [0002] With the continuous development of space technology, more and more countries are launching spacecraft. Moreover, the progress of advanced technologies such as microelectronics and the application of small high-performance electronic components have further miniaturized small satellites. Then the concept of CubeSat was born. It was first proposed by Professor San Luis Obispo of Caltech University and Professor Bob Twiggs of Stanford University in 1999. A cube with a side length of 10cm is used as a standard unit, which can be flexibly configured into a unit according to mission requirements. , double unit, triple unit, etc. Different from mission-oriented spacecraft design, CubeSat has formulated a series of standards including structure, electrical interface, test process, and working mode defin...

AI Technical Summary

Problems solved by technology

[0007] The current design of the cube star bias momentum attitude control system structure occupies too much space in the cube star, reaching 1U or even 1.5U, which is not suitable for a cube star with a size of only 1U or 2U. Due to the internal size constraints and the system circuit connection, the design of the bias momentum attitude control system in the prior art is complicated and the system cannot be designed independently. The system needs to be redesigned according to different satellites, and the system reliability is not high.

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