| With the space exploration and the numerous spacecraft launching, a growing number of failure of the aircraft become increasingly serious problem due to the reasons of space junk. In order to deal with this problem, active removal technology has become the inevitable choice.Many organizations or individuals explore many ways to remove the spacecraft space debris or failure aircraft. Due to the failure of the spacecraft in space may have a large rotation of the angular velocity, it is a great security challenges to capture and recycling. In this dissertation, choosing a way of using the initiative coulomb actuation to control the relative attitude of space debris or failure of the spacecraft. In the process of analysis and the aircraft flight dynamics model and the stability of the system.In the first place, this dissertation analysis the environment of the flight spacecraft and discusses the Debye shielding. And talk about the process of charging and disturbance. With the condition of the hypothesis, that the center of mass of the model, with the coulomb force influence, how the spacecraft formation kinetics model is set up.Considering the complexity of the despun target, in this dissertation, a common cylinder model approximate the multi sphere modeling(MSM).With the study of this simplification of the spacecraft model, discussing the coulomb force with the influence of active spacecraft to analyze failure of spacecraft and the torque. Establish the coulomb force despun dynamics model with the distance of two spacecraft in 15 meters.Learning the Spacecraft formation may have perturbation in the process of formation flight, considering the spacecraft is in orbit on tangent movement,it is necessary to analyze its stability. With the analysis of the design of feedback control, the relative position of spacecraft in orbit direction deviation need to control.Finally, attitude control stability is analyzed in this dissertation.Considering the spacecraft is in orbit and the action of coulomb force required the rate control. Therefore, the two spacecraft with a distance of 15 meters ofthe despun efficiency simulation analysis. And we has obtained the ideal control effect.This scheme can also be applied to the spacecraft rendezvous and docking with a little modification, or formation flight and spacecrafts. |
