Abstract
Vibration suppression during attitude control is a fundamental research topic whenever control of the rotational motion of a spacecraft with flexible appendages and internal liquid sloshing is of interest. The proposed method is based on an attitude control system with centralized sensors and actuators, without the usage of collocated devices for vibration management. In this way, it is possible to develop and implement a computationally efficient real-time control system that is suitable for any kind of spacecraft, even with advanced control capabilities. An integrated vibration suppression attitude control is designed and analyzed, exploiting also a numerical simulation verification procedure based on validated code. The developed attitude control system applies two fundamental control schemes: classical proportional-derivative (PD) control, with nonadaptive band-stop filters, and wave-based control. The proposed wave-based control implementation allows managing three-dimensional attitude dynamics in steady state pointing, without cross-coupling between the separate body axes. To overcome this limitation, the paper presents the integration of the wave-based control with the filtered PD control scheme, allowing us to have a complete three-dimensional real-time MIMO controller, with vibration suppression capabilities and robustness to system uncertainties. The paper also presents the development of an accurate dynamical model of a generic flexible spacecraft with internal liquid sloshing based on a multibody formulation.
Highlights
Vibration suppression during attitude control of flexible spacecrafts with internal liquid sloshing is an active research topic intriguing the space engineering community for manyA
Even if it is reasonable to decouple the natural orbital dynamics from the flexible effects, the rotational dynamics is frequently affected by internal system vibrations
Whenever an attitude control system (ACS) is considered and the study is focused on forced dynamics, the assumption to decouple flexible and rotational dynamics is even less valid
Summary
The possibility to have a dynamic vibration compensation that uses only attitude and angular velocity measures as sensors and piezoelectric patches as actuators was proposed by Di Gennaro [2] These approaches exploit the smart structure design allowing the use of decentralized or hierarchical control strategies, but they rely on a system that is more complex and less prone to be integrated in applications requiring an extremely high reliability with cost effectiveness, such as small space platforms. In order to avoid dangerous resonances and vibrational excitations, which may result in a reduction of the achievable performances of the control, or in a loss of the attitude stability [25], the PD control is integrated with nonadaptive bandstop notch filters, maintaining the computational efficiency and the reliability of the method This method lacks dedicated vibration suppression capabilities and it is not robust with respect to system modeling errors and parameter uncertainty. The two approaches can be used together to assemble and simulate any kind of flexible space structures because of the multibody formulation of the proposed model
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