Solar Wing Motor-driven Vibration Control Theory And Simulation

Attitude control of solar array panel excites satellite's dynamic structural vibrations, which will influence satellite's proper operation. There're two traditional techniques to solve this vibration damping problem, one is passive vibration reduction, and another is active vibration reduction. Constrained by structural mass and material property, passive vibration reduction techniques always have their limits in solar array panel's vibration control.How to increase system's vibration damp via active vibration control, in order to fast control the solar array panel's residual oscillation is this article's major research subject, which include following several key points:1) Start from the classic vibration theory derivation to find an active control technique based on velocity feedback, which will increase the system's vibration damping coefficient thus accelerate the damping of residual oscillation.2) Based on one science paper's eigenvalue assignment methods for the symmetric definite quadratic pencil, bring this potential control method into the two order linear oscillation system, trying to achieve the target of increase the vibration damping for the system.3) In order to validate above two active control techniques, simplifying the solar array panel into a beam model, and then apply the feedback control scheme into Nastran's finite element analysis, using the numerical computation results to validate those two control systems'efficiency.4) With previous theory analysis and consecutive finite element simulations'results, considering both the plate's bending and twists effect to closely match the solar array panel's actual working situation, further develop and validate the eigenvalue assignment control technique.