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dc.contributor.supervisor Ferguson, Philip (Mechanical Engineering) en_US
dc.contributor.author Parthasarathy, Varsha
dc.date.accessioned 2021-01-13T18:14:41Z
dc.date.available 2021-01-13T18:14:41Z
dc.date.copyright 2021-01-12
dc.date.issued 2021-01-02 en_US
dc.date.submitted 2021-01-02T21:55:18Z en_US
dc.date.submitted 2021-01-12T23:43:19Z en_US
dc.identifier.uri http://hdl.handle.net/1993/35224
dc.description.abstract Low-earth orbit satellite constellations provide important services over very large areas in a uniform way. Traditional spacecraft communication typically requires manually-staffed ground stations with space systems experts controlling and monitoring bus and payload systems during each pass. These onerous requirements limit the ability to access valuable space assets, more so in the case of large constellations of satellites. This thesis presents a virtual ground station (VGS) with a real-time virtual satellite model (VSM) and a fault-management system based on industrial statistical process control (SPC) techniques and time-domain feature extraction. The VSM is in continuous view of the VGS at all times and allows the operators to send and receive data as required without waiting for a pass. The operators always interact with the VSM through a graphical user interface (GUI) terminal as opposed to the spacecraft itself such that the VSM mimics the actual satellite as much as possible. The VGS streamlines spacecraft operations by managing every real pass, uploads stored commands when a pass occurs, automatically downloads telemetry and maintains the VSM. This eliminates trivial housekeeping activities and lets the experts focus on complex problems. The VGS also contains a real-time orbit propagator that provides the real-time position and velocity of the satellite and lets the operators visualize the mission in 3D. In this thesis, the VSM uses the power subsystem as an example and takes the form of a real-time power subsystem simulator of the spacecraft. The fault-management system employs custom algorithms to monitor telemetry from the spacecraft and compare it to the predicted telemetry from the VSM to perform early fault diagnosis. The specific faults considered are the loss of a solar string(s), increase in the battery's internal resistance and excessive power consumption onboard the spacecraft. A unique testbed consisting of a simulation engine with an actual satellite model (ASM) and a serial communication protocol is presented. It is used to demonstrate the functions of the VGS through various scenarios during a typical interaction between the VGS and the satellite. Some of these scenarios include initiation of communication with the spacecraft, automatic telemetry downloading, anomaly detection, real-time data requests and storing and uploading commands to the spacecraft. en_US
dc.rights info:eu-repo/semantics/openAccess
dc.subject Spacecraft constellations en_US
dc.subject Ground stations en_US
dc.subject Fault-detection en_US
dc.subject Real-time health-monitoring en_US
dc.subject Statistical process control en_US
dc.subject Virtual model en_US
dc.subject Power subsystem en_US
dc.subject CubeSat simulator en_US
dc.subject Graphical user interface en_US
dc.subject Operations application en_US
dc.subject Automation en_US
dc.subject Virtual satellite model en_US
dc.subject Automated telemetry analysis en_US
dc.subject Feature extraction en_US
dc.title Virtual ground station for automated spacecraft operations en_US
dc.type info:eu-repo/semantics/masterThesis
dc.type master thesis en_US
dc.degree.discipline Mechanical Engineering en_US
dc.contributor.examiningcommittee Liang, Xihui (Mechanical Engineering) Bellili, Faouzi (Electrical and Computer Engineering) en_US
dc.degree.level Master of Science (M.Sc.) en_US
dc.description.note February 2021 en_US


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