An attitude recovery technique for momentum biased satellites is presented. It applies to anomalies in which no significant external torques act on the satellite and hence the total angular momentum vector is conserved. The technique is based on a control law which minimizes the spin energy of the satellite body using the momentum wheel as the only actuator. It requires only reasonably accurate estimates of spacecraft inertias, which can be determined in orbit by a method described. By the inclusion of a first order predictor the control loop is shown to cope with significant delays in data acquisition and control implementation. The recovery technique is therefore suitable for implementation on-board or under ground control. An experiment demonstrates its effectiveness with ESA's communications satellite OTS.
In-Orbit Demonstration of Recovery from Flat Spin for a Momentum Bias Controlled Communications Spacecraft: OTS
1986
6 pages
Report
Keine Angabe
Englisch
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