Abstract
Aiming at the oscillation suppression of spacecraft with large flexible appendages, we propose a control strategy using H∞ control. The weighting functions are designed for the specific flexible modes of the spacecraft and the frequency of harmonic interference in its operating environment. Taking into account the structural uncertainty of systematic modeling and the comprehensive performance requirements of system bandwidth constraint and attitude stability, the H∞ comprehensive performance matrix is constructed. A space telescope with a large flexible solar array is presented as an illustrative example, and a control design that meets the requirement for pointing accuracy is proposed. The simulation results show that the designed controller satisfies the requirements of attitude stability and high pointing accuracy and has effectively suppressed the disturbance of endemic frequency. The design scheme and selection method of the weight function shown in this paper can be a reference for the controller design for oscillation suppression of this type of spacecraft with flexible structures.
Highlights
A spacecraft with flexible appendages, such as a spacecraft carrying large flexible solar panels, has a system structure with multiple resonance modes. e resonance mode of this type of flexible system changes its amplitude characteristics greatly, and the choice of bandwidth is greatly restricted by the inherent low-frequency interference caused by the complex launch environment and the high-altitude environment during on-orbit operation and the flexible mode of the system itself [1,2,3]. e difficulty of the control design of this kind of flexible system is to suppress the inherent resonance interference and to meet the control accuracy requirements, as well as to take into account the requirements of attitude stability and bandwidth limitation of the system [4, 5]
A notch filter in series with a PID controller is used to achieve stability control and interference suppression, and an internal model controller is connected in series to suppress the unique resonance interference. e proposed controller can suppress the resonant mode of the particular frequency well, but it cannot take into account the stability and robustness of the system. e research shows that it is difficult to use classical control to balance the multiple performance requirements for the integrated control of Complexity flexible spacecraft with multiple performance requirements [8]
A space telescope with large flexible appendages, illustrated in Figure 1, is composed of gyros that provide speed and attitude information, precision guidance sensors and trackers that supplement the attitude information, reaction wheels that provide control torque, and two large flexible solar panels carried on the other side
Summary
A spacecraft with flexible appendages, such as a spacecraft carrying large flexible solar panels, has a system structure with multiple resonance modes. e resonance mode of this type of flexible system changes its amplitude characteristics greatly, and the choice of bandwidth is greatly restricted by the inherent low-frequency interference caused by the complex launch environment and the high-altitude environment during on-orbit operation and the flexible mode of the system itself [1,2,3]. e difficulty of the control design of this kind of flexible system is to suppress the inherent resonance interference and to meet the control accuracy requirements, as well as to take into account the requirements of attitude stability and bandwidth limitation of the system [4, 5]. E difficulty of the control design of this kind of flexible system is to suppress the inherent resonance interference and to meet the control accuracy requirements, as well as to take into account the requirements of attitude stability and bandwidth limitation of the system [4, 5]. Aiming at the system’s specific interference frequency, the corresponding H∞ weighting function is designed to achieve disturbance attenuation and the H∞ controller that satisfies the robustness and attitude stability of the system is given. E design scheme and selection method of the weight function shown in this paper can be a reference for the controller design for oscillation suppression of this type of spacecraft with flexible structures. Aiming at the system’s specific interference frequency, the corresponding H∞ weighting function is designed to achieve disturbance attenuation and the H∞ controller that satisfies the robustness and attitude stability of the system is given. e simulation results show that the controller designed in this paper can suppress the resonance interference in the spacecraft natural frequency and satisfies the stability and bandwidth constraints. e design scheme and selection method of the weight function shown in this paper can be a reference for the controller design for oscillation suppression of this type of spacecraft with flexible structures. e structure of this paper shows that the system model and control problems are briefly described in Section 2, and the performance requirements of the H∞ design and the selection scheme of the weighting function are shown in Section 3; Section 4 is a performance analysis, and Section 5 is the conclusion
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