| タイトル | Orbital Injection of the SEDSAT Satellite: Tethered Systems Dynamics and Flight Data Analysis |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960021018 |
| 著者（英） | Gullahorn, Gordon E.; Pelaez, Jesus; Ruiz, Manuel; Cosmo, Mario L.; Lorenzini, Enrico C. |
| 著者所属（英） | Smithsonian Astrophysical Observatory |
| 発行日 | 1996-04-01 |
| 言語 | eng |
| 内容記述 | This report deals with the following topics which are all related to the orbital injection of the SEDSAT satellite: Dynamics and Stability of Tether Oscillations after the First Cut. The dynamics of the tether after the first cut (i.e., without the Shuttle attached to it) is investigated. The tether oscillations with the free end are analyzed in order to assess the stability of the rectilinear configuration in between the two tether cuts; analysis of Unstable Modes. The unstable modes that appear for high libration angles are further investigated in order to determine their occurrences and the possible transition from bound librations to rotations; Orbital Release Strategies for SEDSAT. A parametric analysis of the orbital decay rate of the SEDSAT satellite after the two tether cuts has been carried out as a function of the following free parameters: libration amplitude at the end of deployment, deviation angle from LV at the first cut, and orbital anomaly at the second cut. The values of these parameters that provide a minimum orbital decay rate of the satellite (after the two cuts) have been computed; and Dynamics and Control of SEDSAT. The deployment control law has been modified to cope with the new ejection velocity of the satellite from the Shuttle cargo bay. New reference profiles have been derived as well as new control parameters. Timing errors at the satellite release as a function of the variations of the initial conditions and the tension model parameters have been estimated for the modified control law. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | 96N24510
NASA-CR-200904
NAS 1.26:200904 |
| 権利 | No Copyright |
