OTS-2: End-Of-Life Dynamics Tests
£5.00
I. T. Mitchell. (1992), JBIS, 45, pp.57-62
Refcode: 1992.45.57
Abstract:
Attitude stabilisation for the OTS spacecraft is achieved through use of a single momentum wheel aligned on the pitch axis, nominally parallel to the orbit normal. This arrangement is often used on Earth-pointing spacecraft and such spacecraft are referred to as being momentum biased. In this arrangement the momentum wheel maintains a large angular momentum to provide short term stability against the influence of disturbance torques. The momentum wheel also permits yaw attitude stabilisation through the roll-yaw quarter-orbit coupling without requiring a yaw attitude sensor and provides an actuator for pitch control.
