A CubeSat Bias Momentum Attitude Control System

Abstract

The invention discloses a cubic star bias momentum attitude control system, which comprises a mounting frame, a base, a control module and a measurement and control assembly. And the control assembly includes two offset momentum wheels, four sun sensors, three-axis magnetic torque device, gyroscope, GPS receiver and two-way magnetometer, two offset momentum wheels are fixed in the installation frame, four The sun sensor is respectively fixed on the four outer sides of the installation frame, the gyroscope is fixed in the base, and the GPS receiver and the two-way magnetometer are integrated on the control module. The system of the present invention is small in volume and high in functional density, and the four-corner through holes reserved by the system can be fixed in the cube star through studs, which is suitable for the design standard of the existing cube star, and the installation space of two offset momentum wheels is reserved inside the system , Integrating two-way magnetometers in the control circuit board can effectively improve the reliability of the attitude control system.

Description

Technical field[0001]The present invention relates to the field of cubic stars, and more particularly to a cubic star offset momentum attitude control system.Background technique[0002]With the continuous development of aerospace technology, the number of launched spacecrafts in countries have increasingly. And advanced technologies such as microelectronics, the application of small high-performance electronic components, making small satellite further miniaturize. The birth of the birth cube satellite concept, the earliest proposal by Professor San Luis Obispo, California University of Science and Technology, and Professor of Stanford University BOB TWIGGS, jointly proposed, with a standard unit, according to the task demand, can be flexible according to the task requirements , Double unit, three units, etc. Unlike the task-oriented spacecraft design, cube satellite has developed a series of standards including structural, electrical interface, test procedures, and working mode defi...

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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