Hardware Design And Semi - Physical Simulation Of Stereo Determining And Controlling System

CubeSat has been developed rapidly in recent years. It has become an important branch of spacecraft. Attitude determination and control system, which is used for the realization of the measurement and control of satellite attitude, is an important guarantee to realizes the function of a CubeSat. This paper focuses on the designing the ADCS of the NJUST-1 double unit CubeSat, which includes three-axis magnetometer design, test and error correction, magnetorquer design and test, momentum wheel design and test. The main Contents are summarized as follows:This paper analyses the overall mission of NJUST-1 CubeSat and devises the scheme of ADCS subsystem, which uses a magnetometer as the main attitude measurement instrument. Six coarse sun sensor are supplemented in order to achieve the dual vector attitude determination. The pitch bias momentum wheel and the three-axis magnetorquer are used as attitude control instrument.Secondly, the paper focuses on the detailed design of ADCS Hardware, including magnetometer and magnetorquer and momentum wheel. The magnetometer, whose power consumption is less than 200mW, uses high density circuit design and integrated EMC design, to achieve ultra-small volume. The magnetometer integrated error correction theory and theme which helps decreases the total error by two orders of magnitude, is an effective solution to solve the interference of satellite remnant magnet in magnet measurement. The design of the three-axis magnetorquer with magnetic core greatly reduce the system power consumption. The H bridge circuit is used for the current-time control and enhance the efficiency. The designed magnetic moment is 0.15Am2. The power consumption is less than 500mW. The momentum wheel uses a DC brushless motor and mass block. Through parameter optimization, Ultra small volume and low power consumption is realized. Designed angular momentum is 2mNms. It can be used in other micro satellite mission.Finally, a semi-physics simulation system is built to testify the design of the ADCS subsystem. The simulation results meet the design parameter. And in-orbit data is presented to verify the correctness of ADCS design and simulation.