| Summary: | With the developments in space technology, the capabilities of spacecrafts have been
increased considerably which in turn have entailed the development of more efficient
spacecrafts in terms of cost, mass, size and power. One way to achieve such a development
is the replacement of body mounted appendages with the deployable ones, which greatly
reduces the size, mass and cost of the spacecraft especially when large appendages are
considered. In order to obtain these deployable structures, deployment mechanisms and
deployment mechanism drivers are used. A deployment mechanism is a combination of
electrical and/or mechanical structures which hold the appendages in the stowed position
before launch and deploys them after the launch with the power and commands supplied by
the deployment mechanism driver. This necessary power of the deployment mechanism
driver is produced by the Power Stage of the deployment mechanism driver and the
necessary commands required by the deployment mechanism are supplied by the Control
Stage of the deployment mechanism driver. In this thesis, the power stage of a deployment
mechanism driver will be designed and implemented taking into account of the
requirements for Low Earth Orbit Satellites such as temperature tolerance, reliability and
radiation limits. In order to acquire a cost, mass and size efficient Power Stage, different
deployment mechanism topologies will be studied and the most convenient one among
these topologies will be chosen as the deployment mechanism driver load and the design
will be performed accordingly.
|
|---|
