Abstract
The paper deals with the deployment dynamics of a tethered spacecraft with the consideration of attitude motion. The flexible tether is modeled through a sequence of lumped masses connected by viscoelastic dampers, and the spacecraft as a rigid body. According to Newtons law, the time-varying equations of motion of the system for deployment and retrieval are obtained. Then, the attitude dynamics of spacecraft during deployment are numerically investigated based on the Kissels deployment strategy. The results show that the deployment dynamics is greatly dependent on the initial attitude angle of spacecraft. If without control action on tethers deployment, the impulse arisen form the velocity jump at the end of deployment will cause the spacecraft to rotate, and an oscillation occurs around the local equilibrium of spacecraft as the Kissels control is applied during deployment of the tether.
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