Flexible Satellite Attitude Maneuver via Adaptive Sliding Mode Control and Active Vibration Suppression

Observer-based multi-objective parametric design for spacecraft with super flexible netted antennas

“…(1) Different from many existing control methods that is proposed for a single objective (e.g., [2][3][4][5][6][7][8], [11][12][13][14][15][16][17][18][19][20][21]), this paper considers multi-objective design issues, and it aims to make the closed-loop system have simultaneously lower eigenvalue sensitivity, and also it aims a smaller control gain and a stronger tolerance for high-order unmodeled dynamics and disturbances.…”

“…However, these results are mostly inexplicit, and are inconvenient to use. Prof. Duan established for linear systems complete parameterizations of stabilizing state and output feedback controllers in general explicit closed forms in the early 1990's [1][2][3][4][5][6], and later on extended the results to different types of systems and more complicated controllers [1,2,[7][8][9][10]. A great feature of his formulas is that closedloop eigenvalues are explicitly appeared as part of the design degrees of freedom, and general parametric expressions of the closed-loop eigenvectors are also provided.…”

“…For example, in 1958 the satellite named "Explorer-1" caused the energy dissipation in the system owing to the flexible vibration of the four whip antennas that eventually led to the attitude roll [1]. Therefore, vibration suppression and attitude control of spacecraft with large flexible attachments is a critical problem and it has received lots of attention [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21]. Sliding mode control (SMC) and backstepping control are commonly used control methods in order to solve this problem.…”

“…In [4], a robust control algorithm was proposed for stabilization of a three-axis stabilized flexible spacecraft in the presence of parametric uncertainty, external disturbances and control input nonlinearity/dead-zone. For more up-to-date results about applications of SMC and backstepping methods in flexible satellite attitude control, readers can refer to [6][7][8]. Robust H ∞ control is another effective control method for flexible spacecraft control.…”

“…In addition to SMC, backstepping, and robust H ∞ control, many other control methods are also applied to the vibration suppression and attitude control of flexible satellites, such as disturbance observer-based control [13][14][15], adaptive control [16][17][18][19][20], and finite-time control [16,18,21]. Many of the current control methods are proposed for a single control target (e.g., [2][3][4][5][6][7][8][11][12][13][14][15][16][17][18][19][20][21]) to provide flexible spacecraft control. However, in actual engineering, we need to consider the accuracy, rapidity, smoothness, the influences of parameter perturbations, and high-order unmodeled dynamics at the same time.…”