## 1 Introduction
However, this approach assumes that all periods of disturbances should be known, which is difficult in practical engineering. Although the preceding strategies have made some achievements in disturbance rejection, parameter magnitudes considered in research, like the variation range of disturbance frequency and disturbance amplitudes, are not large enough. Furthermore, corresponding experiments verifying their effectiveness are absent in most literature, and it is unpractical to output complicated desired compensating torques by any actuators. Maneuver actuators may also affect the attitude accuracy. Speaking of the actuators, jet thrusters are inappropriate for persistent disturbance. Reaction wheels are extensively used due to their advantage in generating continuous and precise torques without expending the propellant [17; 18]. Although it is easy for torque mode reaction wheels to output a constant value torque, evident faults exist when tracking an expected time varying torque [19]. Most of the present papers failed to consider the capability of reaction wheels. These complex control output torques may be unfulfillable in common practical engineering. On the other hand, problems like time delay may be solved by the using of flywheel actuators. [PERSON] et al. [20; 21] tackled the problem of controlling time delayed systems. A prediction of state at the time of the control application has been performed to compensate for the time delay. A Kalman filter and the GNC loop were used to realize this purpose. [PERSON] et al. also conducted research to test and improve the robustness of presented algorithm. Simulations and experiments were provided to confirm the effectiveness. Those works may cover the shortage caused by the time delay. Further, for meteorological satellites in the presence of known laws of periodic disturbances, those methods are inappropriate and superfluous. Based on those facts, for the compensation of periodic disturbed torques, constant reaction wheel torques may be the most practical and appropriate way. Unfortunately, work is limited on this issue in the literature. Another way to improve the attitude accuracy of meteorological satellites is to actively suppress the residual vibrations of flexible appendages. This kind of strategy has been widely used in the attitude maneuver of spacecraft. Numerous studies have been presented for vibration suppression of flexible appendages. Smart materials, such as Magnetorheological Material (MR) [22], Piezoelectric Material (PM) [23; 24], have been investigated and fabricated to eliminate the residual vibrations during the past decades. A wide range of control schemes has been proposed for the use of smart materials, such as positive position feedback (PPF) control [25], sliding mode control (SMC) [26], H-infinity control [27], and so on. However, these actuators and sensors have changed the structural property by mechanical interference, which is undesirable in many practical engineering applications. An active vibration suppression method called component synthesis vibration suppression (CSVS) can suppress vibration without additional structures attached to flexible structures. This method was first proposed by [PERSON] et al. [28]. Then, [PERSON] et al. [29] extended the application of the CSVS method in the attitude maneuver of spacecraft. However, as a feedforward control scheme, the application of the CSVS method is limited to the sensitivity to parameter uncertainties. Similar to the CSVS method, the input shaping technique is also used for vibration suppression. [PERSON] et al. [30] extended the input shaping method by combining it with feedback control for the vibration control of flexible spacecraft during attitude maneuver. Their work remedied the shortcoming of input shaping as it is a feedforward control scheme. However, this technique is suitable for zero to zero maneuver. It is not appropriate for problems forced in this paper in which the disturbance is nonstop.