Dynamic Modeling And Attitude Control Of Flexible Spacecraft

In this paper, a class of flexible beam attachment with rod-shaped spacecraft is studied.Firstly,the dynamic equation is established. The flexible appendage of spacecraft equation derived the Lagrange equation is established and differential dynamic equations are formed. With modal analys , the dynamic equation normalized.Free vibration and PD control style is simulated.Simplify the modeling process with no influence,make the following assumptions,ignore the gravity of the spacecraft,the main body is cylindrical rigid body spacecraft and it only make single-axis rotation.In view of the space environment is complex,the structure is vulnerable to all kinds of interference,and it is very easy to be provoked large amplitude vibration,position feedback compensator is introduced to increase the system damping.Adopt the PD control combine positive position feedback algorithm to control the attitude of the main body, the simulation result is that the system damping become larger.Jet thrusters as the implementing only have control torque with limited amplitude.The Pulse Width Pulse Frequency (PWPF) is introduced, it is combined the attitude control of flexible spacecraft,the PD and VSC control algorithm is invented with PWPF actuator. The simulation result is that vibration displacement of the flexible end-point is smaller,but the setting time become larger.