Slewing Flexible Spacecraft with Deflection-Limiting Input Shaping

Abstract

A control scheme is described for slewing exible spacecraft with both suppression of de ection during the slew and elimination of residual oscillations. The method minimizes the maneuver time subject to constraints on residual vibration magnitude, sensitivity to modeling errors, rest-to-rest slew distance, and the transient de ection amplitude. Furthermore, a solution is sought that provides inherent fuel ef ciency. The feasibility of the approach is demonstrated with linear and nonlinear computer simulations.

Experiments on Command Shaping Control of a Manipulator with Flexible Links

“…3) The maximum value of the smoothing parameter has been considered (® D 0:25), and the joint angular accelerations obtained by Eqs. (2) for RA 3 , smoothed bang-bang. 4) Again the three-impulses input shaper has been applied for RA 4 , input shaping applied to the smoothed bang-bang pro le.…”

“…They 2 obtained promising simulation results of input shaping control of the space shuttle remote manipulator system. Singhose et al 3 studied an input shaping controller for slewing a exible spacecraft. Banerjee and Singhose 4;5 proposed the application of input shaping for the minimum-time control of a two-link exible manipulator.…”

Model Predictive Control for Deflection-Limiting Maneuver of Flexible Structure

“…In order to limit deflection or a bending moment of the flexible appendage during maneuvers, the deflection-limiting control, 9) minimum bending-moment control 10) and its application to the multiobjective optimization control 11) have been proposed. The original deflection-liming control method, 9) however, was not robust to modeling errors, because it did not integrate an adaptive method. To overcome this disadvantage, an adaptive deflection-limiting control 12) has been proposed.…”

Multi-Objective Trajectory Optimization by a Hierarchical Gradient Algorithm with Fuzzy Decision Logic-Application to Slew Maneuver Problems of a Flexible Space Structure-

“…The time optimal control problem for flexible space structures is one example of such research; various methods for suppressing vibration of flexible space structures have been proposed [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16] and experiments were carried out. [17][18][19] Singhose et al, 10,11) Singer and Seering 12) and Rogers and Seering 13) have studied the input shaping method, which is the open-loop control method and does not induce vibration on flexible space structures much by using a frequency shaped command. Singhose 11) has also proposed the method that not only minimizes maneuver time, but also restrains the deflection of the flexible appendage under a considered value in order to suppress the load affecting the flexible appendage during maneuver.…”

“…[17][18][19] Singhose et al, 10,11) Singer and Seering 12) and Rogers and Seering 13) have studied the input shaping method, which is the open-loop control method and does not induce vibration on flexible space structures much by using a frequency shaped command. Singhose 11) has also proposed the method that not only minimizes maneuver time, but also restrains the deflection of the flexible appendage under a considered value in order to suppress the load affecting the flexible appendage during maneuver. We have proposed a minimum bendingmoment control (MBMC) method in which the maximum value of the bending moment induced on the root of the flexible appendage is restricted (in addition, the L2 norm of the bending-moment is minimized during maneuver), and experimentally verified the validity of the method.…”