Global ETD Search

1	VHF Beacon Development, Ground Segment, and Operations for CanX Missions Shah, Amee 15 February 2010 (has links) The versatile Generic Nanosatellite Bus (GNB) technology fused with the Canadian Advanced Nanospace eXperiment (CanX) missions is pioneered by the Space Flight Laboratory (SFL) at University of Toronto Institute for Aerospace Studies. Microspace philosophy has been employed at SFL to develop low cost nanosatellites with emerging technologies for education and research. This thesis provides an insight to the space systems engineering experience acquired by the author being a master’s student at SFL. This thesis describes the design, construction and testing of the VHF beacon transmitter for GNB. The umbilical Electrical Ground Support Equipment (EGSE) designed and built by the author is presented in this thesis. The assembly, integration and testing of the SFL ground station for the CanX missions has been explored. The on-orbit spacecraft operations for CanX-2 and NTS, from the launch campaign to the commissioning phase to nominal operations along with the anomalies faced and the contingency operations carried out by the author to date have been explained in detail in this thesis. CanX nanosatellite beacon operations 0538
2	VHF Beacon Development, Ground Segment, and Operations for CanX Missions Shah, Amee 15 February 2010 (has links) The versatile Generic Nanosatellite Bus (GNB) technology fused with the Canadian Advanced Nanospace eXperiment (CanX) missions is pioneered by the Space Flight Laboratory (SFL) at University of Toronto Institute for Aerospace Studies. Microspace philosophy has been employed at SFL to develop low cost nanosatellites with emerging technologies for education and research. This thesis provides an insight to the space systems engineering experience acquired by the author being a master’s student at SFL. This thesis describes the design, construction and testing of the VHF beacon transmitter for GNB. The umbilical Electrical Ground Support Equipment (EGSE) designed and built by the author is presented in this thesis. The assembly, integration and testing of the SFL ground station for the CanX missions has been explored. The on-orbit spacecraft operations for CanX-2 and NTS, from the launch campaign to the commissioning phase to nominal operations along with the anomalies faced and the contingency operations carried out by the author to date have been explained in detail in this thesis. CanX nanosatellite beacon operations 0538
3	Ground Segment Software Design and Development for Nanosatellite Space Missions Choi, Jin Hyouk 18 March 2013 (has links) For spacecraft development, realizing strong supporting ground segment software is as important as designing the actual hardware component of the spacecraft. This thesis describes the author’s contributions to the ground segment software design and development for nanosatellite space missions at the UTIAS Space Flight Laboratory. Particular emphasis is given to the ground segment software for the CanX-3 and CanX-4/-5 missions. For the CanX-3 mission, several software applications are explored, specifically ground control software for the payload on-board computer and star tracker, and mission planning software. For the CanX-4/-5 mission, its mission monitor and control software, and whole orbit data parser are discussed. For each software application, design considerations and decisions made during the development are explained. Furthermore, detailed discussions on their architectural and graphical user interface design and implementation are presented. nanosatellite ground segment ground software ground station CanX-3 CanX-4/-5 0538
4	Ground Segment Software Design and Development for Nanosatellite Space Missions Choi, Jin Hyouk 18 March 2013 (has links) For spacecraft development, realizing strong supporting ground segment software is as important as designing the actual hardware component of the spacecraft. This thesis describes the author’s contributions to the ground segment software design and development for nanosatellite space missions at the UTIAS Space Flight Laboratory. Particular emphasis is given to the ground segment software for the CanX-3 and CanX-4/-5 missions. For the CanX-3 mission, several software applications are explored, specifically ground control software for the payload on-board computer and star tracker, and mission planning software. For the CanX-4/-5 mission, its mission monitor and control software, and whole orbit data parser are discussed. For each software application, design considerations and decisions made during the development are explained. Furthermore, detailed discussions on their architectural and graphical user interface design and implementation are presented. nanosatellite ground segment ground software ground station CanX-3 CanX-4/-5 0538
5	Reconfiguration and Recovery of Formation Flying Spacecraft in Eccentric Orbits Roscoe, Christopher William Thomas 22 September 2009 (has links) The problem of reference trajectory reconfiguration and long-term uncontrolled recovery of a formation of spacecraft is considered in an eccentric orbit under the influence of the J2 perturbation. Reference trajectories considered are the Projected Circular Orbit, Along-Track Orbit, and their eccentric modifications. Reconfiguration is accomplished using two, finite-pulse thrusts, modeled as impulses. The state transition matrix (STM) is calculated by four methods: (i) analytically from the Hill-Clohessy-Wiltshire equations, (ii) numerical integration using a fourth-order Runge-Kutta method, (iii) from the fundamental matrix of the linearized equations of motion, and (iv) computing the STM for the relative mean orbital elements, the geometric method. Only the geometric method takes into account J2, and it is shown to perform the transfers most accurately of all the methods. The methods are also applied to the reconfiguration maneuvers of the University of Toronto's CanX 4/5 formation flying mission. formation flying state transition matrix canx geometric method 0538
6	Reconfiguration and Recovery of Formation Flying Spacecraft in Eccentric Orbits Roscoe, Christopher William Thomas 22 September 2009 (has links) The problem of reference trajectory reconfiguration and long-term uncontrolled recovery of a formation of spacecraft is considered in an eccentric orbit under the influence of the J2 perturbation. Reference trajectories considered are the Projected Circular Orbit, Along-Track Orbit, and their eccentric modifications. Reconfiguration is accomplished using two, finite-pulse thrusts, modeled as impulses. The state transition matrix (STM) is calculated by four methods: (i) analytically from the Hill-Clohessy-Wiltshire equations, (ii) numerical integration using a fourth-order Runge-Kutta method, (iii) from the fundamental matrix of the linearized equations of motion, and (iv) computing the STM for the relative mean orbital elements, the geometric method. Only the geometric method takes into account J2, and it is shown to perform the transfers most accurately of all the methods. The methods are also applied to the reconfiguration maneuvers of the University of Toronto's CanX 4/5 formation flying mission. formation flying state transition matrix canx geometric method 0538
7	Software for the Canadian Advanced Nanospace eXperiment-4/5 Leonard, Matthew Leigh 20 November 2012 (has links) The CanX-4 and CanX-5 mission currently under development at The University of Toronto Institute for Aerospace Studies Space Flight Laboratory UTIAS/SFL is a challenging formation flying technology demonstration. Its requirements of sub-metre control accuracy have yet to be realized with nanosatellites. Many large technical challenges must be addressed in order to ensure the success of the CanX-4/5 mission. This includes the development of software for an intersatellite communication system, integration and optimization of key formation flying algorithms onto the Payload On-Board Computer as well as the development of a Hardware-In-The-Loop simulator for full on-orbit mission simulations. This thesis will provide background knowledge of the Space Flight Laboratory and its activities, the CanX-4/5 mission, and nally highlight the authors contributions to overcoming each of these technical challenges and ensuring the success of the CanX-4 and CanX-5 mission. CanX Embedded Systems Software Protocol Stack Satellite Communications On-board Computers Software Optimizations Nanosatellites 0544 0538
8	Software for the Canadian Advanced Nanospace eXperiment-4/5 Leonard, Matthew Leigh 20 November 2012 (has links) The CanX-4 and CanX-5 mission currently under development at The University of Toronto Institute for Aerospace Studies Space Flight Laboratory UTIAS/SFL is a challenging formation flying technology demonstration. Its requirements of sub-metre control accuracy have yet to be realized with nanosatellites. Many large technical challenges must be addressed in order to ensure the success of the CanX-4/5 mission. This includes the development of software for an intersatellite communication system, integration and optimization of key formation flying algorithms onto the Payload On-Board Computer as well as the development of a Hardware-In-The-Loop simulator for full on-orbit mission simulations. This thesis will provide background knowledge of the Space Flight Laboratory and its activities, the CanX-4/5 mission, and nally highlight the authors contributions to overcoming each of these technical challenges and ensuring the success of the CanX-4 and CanX-5 mission. CanX Embedded Systems Software Protocol Stack Satellite Communications On-board Computers Software Optimizations Nanosatellites 0544 0538
9	Propulsion System Development for the CanX-4 and CanX-5 Dual Nanosatellite Formation Flying Mission Risi, Benjamin 04 July 2014 (has links) The Canadian Nanosatellite Advanced Propulsion System is a liquefied cold-gas thruster system that provides propulsive capabilities to CanX-4/-5, the Canadian Advanced Nanospace eXperiment 4 and 5. With a launch date of early 2014, CanX-4/-5's primary mission objective is to demonstrate precise autonomous formation flight of nanosatellites in low Earth orbit. The high-level CanX-4/-5 mission and system architecture is described. The final design and assembly of the propulsion system is presented along with the lessons learned. A high-level test plan provides a roadmap of the testing required to qualify the propulsion system for flight. The setup and execution of these tests, as well as the analyses of the results found therein, are discussed in detail. aerospace microsatellite nanosatellite propulsion formation flying canx4 canx5 canx-4 canx-5 canx-4/-5 SFL UTIAS cold-gas thruster satellite CNAPS NANOPS nano sulfur hexafluoride SF6 vibration testing spacecraft environmental testing propulsion testing low earth orbit canx2 canx-2 station keeping orbit maneuver orbital station-keeping liquefied cold-gas propulsion micropropulsion engineering space canadian space flight laboratory canadian advanced nanospace experiment PSLV micro-propulsion thruster interferometry ground moving target indicator on-orbit servicing and inspection 0538

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