Abstract
In underactuated conditions, satellite attitude actuators can deliver a control torque with two components only. The paper develops a general solution for the problem of attitude manoeuver planning for underactuated spacecraft
by means of a sequence of N admissible rotations, where a rotation is considered to be admissible if it takes place around an axis which lies on the plane where the actuator system can deliver a control torque. An exact solution for the sequence of two feasible rotations that provides a desired reorientation is derived, where the minimum angular path sequence can also be identified analytically. The optimal sequence for a higher number of steps is obtained by
means of a numerical optimization procedure. The features of the optimal sequences for increasing values of N are investigated in order to obtain a better understanding of their characteristics.
by means of a sequence of N admissible rotations, where a rotation is considered to be admissible if it takes place around an axis which lies on the plane where the actuator system can deliver a control torque. An exact solution for the sequence of two feasible rotations that provides a desired reorientation is derived, where the minimum angular path sequence can also be identified analytically. The optimal sequence for a higher number of steps is obtained by
means of a numerical optimization procedure. The features of the optimal sequences for increasing values of N are investigated in order to obtain a better understanding of their characteristics.
| Original language | English |
|---|---|
| Pages (from-to) | 554-563 |
| Number of pages | 10 |
| Journal | Journal of Guidance, Control and Dynamics |
| Volume | 34 |
| Issue number | 2 |
| DOIs | |
| Publication status | Published - Mar 2011 |
Keywords
- rotation sequences
- rotation axes