Near-Eigenaxis Rotation Control Law Design for Moving-to-Rest Maneuver

Abstract

The ightdynamicsof rigid aircraftare describedby the following set of eight rst-order differential equations taken from Ref. 10:The wind axis orientation angles ¹ and°are de ned as follows:sin°D cos ® cos¯sin µ ¡ sin¯sin Á cos µ ¡ sin ® cos¯cos Á cos µ sin ¹ cos°D sin µ cos ® sin¯C sin Á cos µ cos¡ sin ® sin¯cos Á cos µ cos ¹ cos°D sin µ sin ® C cos ® cos Á cos µ AcknowledgmentsWe would like to acknowledge partial support for this work by a grant from the Aeronautical Development Agency, Bangalore (India), monitored by T. G. Pai and V. S. Ranganathan; computational facilities provided by Gopal Shevare at

Adaptive Fuzzy PD+ Control for Attitude Maneuver of Rigid Spacecraft

“…In , the Matrosov theorem and Barbalat lemma were adopted to analyze the asymptotical stability of the PD+ attitude control system. Parametric uncertainty, which was not considered in , is common in practical application. Motivated by this practical consideration, Wen introduced an adaptive PD+ attitude control law for the uncertainty of a rigid spacecraft's inertia matrix in .…”

“…For the obtained system, conventional linear control techniques, such as the PD technique, can be applied to achieve the desired closed‐loop system, which simplifies the design of the controller . Consequently, the PD+ technique has been studied extensively in recent years . A PD+ attitude control law of rigid spacecraft for rest‐to‐rest attitude maneuver and move‐to‐rest attitude maneuver were designed in , respectively.…”

“…Consequently, the PD+ technique has been studied extensively in recent years . A PD+ attitude control law of rigid spacecraft for rest‐to‐rest attitude maneuver and move‐to‐rest attitude maneuver were designed in , respectively. In , the Matrosov theorem and Barbalat lemma were adopted to analyze the asymptotical stability of the PD+ attitude control system.…”

Shorter Path Design and Control for an Underactuated Satellite

“…To simply demonstrate a shorter path existence, two cases are considered: (1) a rotation angle exists only on the failed control axis and (2) rotation angles exist around all the axes including the failed axis. For the first case, target (30, 0, 0) degrees in the 3-2-1 set of Euler angles are assumed, and the path length is found as 210 degrees from (9) and (10). To find the length of a shorter path, for example, consider target (30, 30, 0) degrees in the 3-2-1 set.…”

“…In the rotation maneuvers, the magnitude of rotation angles is defined as a path length, and the shortest path can be obtained by the eigen-axis rotation [8][9][10][11][12][13][14]. The path length of sequential submaneuvers in failure modes increases significantly, longer than the one under normal conditions.…”