| タイトル | Expected Deployment Dynamics of Proseds |
| 本文（外部サイト） | http://hdl.handle.net/2060/20030106425 |
| 著者（英） | Cosmo, M. L.; Welzyn, K.; Lorenzini, E. C. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | The control law for The Propulsive Small Expendable Deployment System (ProSEDS) deployment is a modification of the control routine that was successfully used in the flight of SEDS-II. Unlike SEDS, the tether of ProSEDS consists of different sections with different mechanical characteristics. A non-linear control trajectory in phase-space (i.e., the reference profile) is fed forward to the controller to guide the satellite, at the tether tip, to the desired final state under nominal conditions and no external perturbations. A linear feedback control is applied by the brake to keep the actual trajectory as close as possible to the reference. The paper also shows the results of simulations of deployment dynamics with and without noise. The control law has thus far been developed and tested on the ground for the original ProSEDS tether configuration of 15 km. A new reference will have to be designed and tested for other tether configurations. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | AIAA Paper 2003-5095 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
