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 Wysłany: Czw 19:33, 06 Sty 2011 Temat postu: mbt shoes cheap Space Station attitude control and |
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Space Station attitude control and momentum management research
Can be designed to roll / yaw channel control system. 5 Simulation In this section, the simulation analysis without considering the disturbance rejection and considered under the disturbance rejection controller design and performance under the system inertia matrix uncertainty error in the case of the robustness of the controller and the internal model parameters controller performance under the changes. 5.1 does not consider the analysis of disturbance rejection controller design for a space station orbit angular velocity of 1.12X10 rad / s,[link widoczny dla zalogowanych], inertia data: Ix = 1.02X10kg · ITI,. = 8.97X10kg · ITI (39) Iz = 2.50X10kg · ITI Figure 4 shows the ideal situation to control pitch, yaw and roll response curves of the three channels is clearly a very good response, the angular momentum peak in the 4-20kg · m / s range (CMG angular momentum of the three channels can be provided up to 200N · m · s); Figure 5 after the introduction of three-channel control of disturbance response curve shows the input torque disturbance response of each channel to have had a period of oscillation,[link widoczny dla zalogowanych], and the pitch response of the channel was particularly notable. 5.2 consider the disturbance rejection controller of the external disturbance signal mode is exactly equal to the space station orbital angular frequency / 7, when the yaw and roll can not be two channels on the attitude angle disturbance rejection, to take on the yaw and roll attitude direction of angular momentum for disturbance rejection. Figure 6 shows that soon reached a steady state value of yaw angle; yaw direction of the angular momentum oscillation, when the disturbance rejection than did not consider smaller; roll angle amplitude is not considered as when inhibited, rolling island of Bali Chang Z: c = l,[link widoczny dla zalogowanych], s Figure 4 without the interference of the angular velocity,[link widoczny dla zalogowanych], attitude angle, angular momentum curve 22 No. 5 Hu Shan et al: Space Station attitude control and momentum management of 41 *? Chang Z cafe as the angular velocity perturbation in Figure 5, attitude angle,[link widoczny dla zalogowanych], angular momentum, angular momentum direction of the curve is completely suppressed. Figure 5b, 5c can be found, the yaw angle and roll angle of the steady-state values are not 0, the result is so because the base transcript. = Curse = is E Fort disturbance signal component in the tower contains a constant disturbance torque component. So that the system is asymptotically stable to the moment equilibrium posture, not a zero-profile place. Figure 6, under the disturbance rejection to avoid pitch angle, yaw angle, roll angle disturbance attenuation curve of Figure 7 under the pitch, yaw, roll-angular momentum curve 6 Conclusion This paper set up under a small change of attitude motion dynamics / kinematics model CMG momentum management equation combined with the establishment of the state of the control system of the basic model. Disturbance under the control of linear systems the general principle of the decoupling of the pitch channel and roll / yaw channel disturbance rejection were carried out research and discussion.
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