THE ATTITUDE DYNAMICS OF HERMES AFTER TERMINATION OF THREE-AXIS STABILIZATION

Authors
  1. Vigneron, F.R.
  2. Krag, W.E.
Corporate Authors
Communications Research Centre, Ottawa ONT (CAN)
Abstract
In late 1979, Hermes, an experimental geostationary communications satellite, experienced an earth sensor malfunction which resulted in its loss of control and subsequent transition from 3-axis stabilization to spin about its maximum-moment-of-inertia axis. During and after the transition, the sun's reflections from the satellite were detected and monitored at the experimental test site (ETS) for the Ground Based Electro Optical Deep Space Surveillance System (GEODSS) in New Mexico. In the report, the satellite's attitude dynamics are deduced by correlating the GEODSS ETS observations with dynamics analysis and simulation. The transition to spin took about 15 days. Thereafter, the rate of spin decayed to zero in about 70 days due to solar pressure. The GEODSS ETS observations also provide data on the relative misalignment and bending of the two solar sails of the satellite.
Report Number
1354 — Paper presented at the 12th Norad Spacecraft Identification Conference 13-15 Aug 80
Date of publication
15 Feb 1982
Number of Pages
26
DSTKIM No
82-01770
CANDIS No
36258
Format(s):
Hardcopy;Originator's fiche received by DSIS

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