Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Power stage design and implementation of a deploymentmechanism driver for space applications
Download
index.pdf
Date
2012
Author
Özdemir, Başak Gonca
Metadata
Show full item record
Item Usage Stats
205
views
100
downloads
Cite This
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.
Subject Keywords
Electronics.
,
Electrical Engineering.
URI
http://etd.lib.metu.edu.tr/upload/12614058/index.pdf
https://hdl.handle.net/11511/21416
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Modeling, stability analysis and control system design of a small-sized tiltrotor uav
Çakıcı, Ferit; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2009)
Unmanned Aerial Vehicles (UAVs) are remotely piloted or self-piloted aircrafts that can carry cameras, sensors, communications equipment or other payloads. Tiltrotor UAVs provide a unique platform that fulfills the needs for ever-changing mission requirements by combining the desired features; hovering like a helicopter and reaching high forward speeds like an airplane. In this work, the conceptual design and aerodynamical model of a realizable small-sized Tiltrotor UAV is constructed, the linearized state-...
Nonlinear controller designs for a reaction wheel actuated observatory satellite
Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2008)
In this research, nonlinear attitude controllers are designed for a low earth orbit satellite intended to be used in observatory missions. The attitude is represented by the Modified Rodriguez Parameters (MRP) which is a minimal representation providing a fully invertible kinematics. As a difference from the classical satellite models existent in the literature, the model of this work incorporates the dynamics of the reaction wheel (actuator) including a brushless dc motor which is armature controlled. The ...
Forecasting of ionospheric electron density trough for characterization of aerospace medium
Kocabaş, Zeynep; Tulunay, Yurdanur; Department of Aerospace Engineering (2009)
Modeling the ionosphere, where the effects of solar dynamo becomes more effective to space based and ground borne activities, has an undeniable importance for telecommunication and navigation purposes. Mid-latitude electron density trough is an interesting phenomenon in characterizing the behavior of the ionosphere, especially during disturbed conditions. Modeling the mid-latitude electron density trough is a very popular research subject which has been studied by several researchers until now. In this work...
Modelling and controller design of the gun and turret system for an aircraft
Mert, Ahmet; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2009)
Gun and gun turret systems are the primary units of the weapon systems of an aircraft. They are required to hit targets accurately during operations. That is why a complete, high precision control of weapon systems is required. This function is provided by accurate modeling of the system and the design of a suitable controller. This study presents the modeling of and controller design for the gun and turret system for an aircraft. For the controller design purpose, first the mathematical model of the system...
Leo satellites : dynamic modelling, simulations and some nonlinear attitude control techniques
Karataş, Soner; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2006)
In this thesis nonlinear control method techniques are investigated to control the attitude of Low Earth Orbit satellites. Nonlinear control methods are compared with linear control methods. Simulations are done using Matlab and Simulink software and BILSAT-1 parameters are used in the simulations. Reaction wheels are used as the actuator.
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
B. G. Özdemir, “Power stage design and implementation of a deploymentmechanism driver for space applications,” M.S. - Master of Science, Middle East Technical University, 2012.