Power Stage Design And Implementation Of A Deploymentmechanism Driver For Space Applications

• Main Author: Ozdemir, Basak Gonca
• Other Authors: Hizal, Mirzahan
• Format: Others
• Language: Eng
• Published: METU 2012
• Subjects: TK Electronics 7800-8360; deployment mechanism driver space applications
• Online Access: http://etd.lib.metu.edu.tr/upload/12614058/index.pdf

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.