Abstract
In this paper, the non-fragile robust attitude control problem is investigated for flexible microsatellite close-proximity inspection, with external disturbances, parameter uncertainties and input constraints. Firstly, the attitude motion model of microsatellite with flexible appendages is established. Secondly, a non-fragile robust dynamic output feedback controller (RDOFC) with multiplicative gain variations (MGV) is designed to satisfy the multi-objective requirements, including pole assignment, H <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">∞</sub> disturbances attenuation and input constraints. Based on the Lyapunov stability theory, the design of the non-fragile robust H <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">∞</sub> attitude control is formulated as the linear matrix inequality (LMI) condition. Finally, numerical simulations are performed to demonstrate the effectiveness of the proposed controller.
Highlights
The capability of space target inspection in close proximity is the premise of space situational awareness and approaching operations
In practice engineering, the microsatellite suffers from external disturbances in space environments [4], and parameter uncertainties caused by the change of moment of inertia [5]
For the nonconvex problem caused by the coupling term in matrix inequality, compared with the two-step procedure solution performed in [25], we propose a less conservative method by constructing a Lyapunov matrix with some structure, which makes the transformation from the NLMIs to the linear matrix inequality (LMI) more
Summary
The capability of space target inspection in close proximity is the premise of space situational awareness and approaching operations. Due to the inherent advantages of small size and high cost-effectiveness, microsatellites are applied into several space close-proximity inspection missions, such as XSS-11 [1], MiTEx [2], and BX1 [3]. Those missions have stimulated the demand for attitude control capabilities of microsatellites, including higher pointing performance and better robustness. The microsatellite is generally equipped with flexible appendages like large antennas and solar array, and the generated vibration will make the high-accuracy attitude control more complicated. The disturbances and uncertainties will deteriorate the closed-loop stability and attitude control accuracy
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