Design Of Attitude Control System For Nanosat Based On Regional Pole Assignment H₂/H_? Control

With the rapid development of space technology,the application of satellite has been playing a more and more important role in modern communication,national defense construction and scientific research.The nano-satellite is very important in the space mission because of its light weight,small size,new technology,short manufacturing cycle and so on.The design of attitude control system is one of the key technologies of nano-satellite control.Many scholars have done a lot of research in this field,and have made a series of achievements.Therefore,the design of effective control strategies to achieve the attitude control of nano-satellite has become a hot topic in the field of aerospace.First of all,the common coordinate system and the relationship between them are defined in the modeling process.The Euler angle is chosen as the attitude description parameter to design the controller.On the basis of this,the kinematics equations and attitude dynamics equations are established.Secondly,considering the change of the space disturbance moment and the moment of inertia,the main factor that affects the uncertainty of satellite attitude change is the change of the moment of inertia.The model uncertainty caused by the change of the space disturbance moment and the rotational inertia of the star is analyzed.Finally,the regional pole assignment,andH₂/H_?control with regional pole assignmentH₂/H_?control method were studied,based on the Lyapunov stability theorem and Schur theory,through variable substitution,using convex optimization principle,the constraints into a linear matrix inequality constrained convex optimization problem.The correspondingcontroller is designed,and the mathematical model of nano-satellite is simulated in MATLAB,and the feasibility of the design is verified by simulation test.Results show that the design scheme can be realized on the nano-satellite attitude stabilization control,almost no effect on control of satellite interference torque and inertia change of attitude;attitude angle and angular velocity curve is smooth,no radical changes,can achieve ideal control effect.