Design And Implemention Of Micro Satellite Attitude Control System Based On SoPC

With the development of modern micro-satellites,the satellite attitude control system put forward new requirements.Considering the low power consumption,small size,light weight of modern micro-satellite,its attitude control system should not be large and complex.How to design a attitude control system with high integration,good real-time,high reliability and good flexibility under the constraints of limited cost,weight,volume and power is a hot issue in micro satellite design.SoPC technology is applied to micro-satellites to carry out the hardware and software co-design of attitude control system from the point of view of improving the precision,integration,real-time,flexibility and scalability of micro-satellite attitude control system.Firstly,based on the low-cost attitude sensor configuration of magnetometer / solar sensor / gyro,an attitude determination algorithm combining Gauss-Newton and UKF filter is designed,which overcomes the influence of measurement error on the accuracy of attitude determination,and also reduces the computational complexity.For the ground capture control task,the quaternion scalar information is introduced into the traditional PD control law,which realizes the automatic adjustment of the control parameters,which has good control effect and response time both in small and large attitude deviation.Secondly,a microsatellite attitude controller based on Nios? dual core architecture is designed by using SoPC technology.Two Nios II soft cores are embedded in one FPGA to process high speed peripheral communication and complex attitude control algorithm respectively.Design and package a number of peripheral interface IP core and the mathematical operation of IP core,respectively,to achieve multi-channel parallel peripheral communication and attitude control algorithm hardware acceleration.Two kinds of dual-core interactive data are designed,which are applied in different scenarios.A batch-type peripheral communication mechanism is designed to improve the real-time performance of peripheral communication.Finally,the full-physical simulation system of micro satellite attitude control system is built based on the three-axis air floating platform.The IP kernel driver,attitude control software and the PC monitoring software are designed.A series of stand-alone and all-physical simulation experiments are carried out.The test and experimental data show that the proposed system has perfect function,stable performance and high reliability.It can be applied to the actual micro-satellite attitude control system.