Abstract
A now procedure for the synthesis of a control law for the stabilization of spacecraft angular velocity is presented. This control law approximately minimizes both the time required to drive the angular velocity of the spacecraft to zero and the integral of the square of the norm of the angular momentum. Synthesis of the control law in feedback form is discussed. In a computer simulation, results obtained by use of the proposed control are shown to compare favourably with those obtained by use of the optimal control.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 269-277 |
| Number of pages | 9 |
| Journal | International Journal of Control |
| Volume | 8 |
| Issue number | 3 |
| DOIs | |
| State | Published - Sep 1968 |