Minisatellite Attitude Control System Design And Simulation Based On Matlab And FPGA

This paper discusses the design of micro-satellite attitude control system. In the context of the rapid development of space science and technology, research FPGA-based hardware controller simulation and implementation of the stars of the three-axis stabilized attitude control, were hardware circuit simulations.There are a variety of actuators to control the satellite’s attitude, zero momentum reaction wheels is one of them. Through the establishment of the mathematical model, the relationship between export function of its input and output, and thus the feasibility study by FPGA-based controller designed. PID controller is designed to study the effectiveness of the closed-loop control simulation system and its control.Based on Matlab/Simulink timing simulation, through the JTAG interface, features, the FPGA Spartan-3E development board to access the hardware circuit simulation and verification of the final design requirements can be achieved provided for reference data and design processes.Space borne equipment requirements computing speed, and space must be small, so this article is designed PID controller is based on a multiplier logic circuit design. Hardware using Verilog HDL language, to achieve the results were compared based on FPGA star zero momentum wheel attitude control hardware layout design and simulation with Simulink figures, we can draw the designed system is effective and feasible.