The Canadian Advanced Nanospace eXperiment (CanX) program at the University of Toronto's Space Flight Laboratory provides rapid, cost effective access to space through the use of micro- and nanosatellites. The primary focus of this thesis is the development of the CanX-4/-5 nanosatellite mission, which is intended to demonstrate precise, autonomous formation flying. This involves the development of nominal and contingency operations, system budgets, and requirements to produce a complete system architecture. Also described is the assembly, integration, and testing of flight hardware for this mission. In addition, this thesis addresses the on-orbit operation of CanX-2 and CanX-6/NTS, as it relates to operations planning for CanX-4/-5. The ground station operations for these two nanosatellite missions are described, with particular focus on payload operations and contingencies resulting from on-orbit anomalies. This experience is then related to the development of the CanX-4/-5 ground station software architecture.

The Canadian Advanced Nanospace eXperiment (CanX) program at the University of Toronto's Space Flight Laboratory provides rapid, cost effective access to space through the use of micro- and nanosatellites. The primary focus of this thesis is the development of the CanX-4/-5 nanosatellite mission, which is intended to demonstrate precise, autonomous formation flying. This involves the development of nominal and contingency operations, system budgets, and requirements to produce a complete system architecture. Also described is the assembly, integration, and testing of flight hardware for this mission. In addition, this thesis addresses the on-orbit operation of CanX-2 and CanX-6/NTS, as it relates to operations planning for CanX-4/-5. The ground station operations for these two nanosatellite missions are described, with particular focus on payload operations and contingencies resulting from on-orbit anomalies. This experience is then related to the development of the CanX-4/-5 ground station software architecture.

As the potential uses of nanosatellites become apparent, their numbers keep increasing. This is evident at the Space Flight Laboratory (SFL) located at the University of Toronto Institute for Aerospace Studies which has seen a rapid growth in satellite missions in recent years. By leveraging the use of the Generic Nanosatellite Bus developed at SFL, satellites can be rapidly developed to carry science payloads or demonstrate the capabilities of new technologies on orbit. Testing satellite systems in an Earth environment is an important step in qualifying them for space. This thesis describes the development of ground support equipment for testing SFL’s nanosatellite separation system, XPOD, and characterizing the performance of the propulsion system, CNAPS. Also, the thermal behaviour of a pressure regulator valve on CNAPS is examined for various flow conditions.

As the potential uses of nanosatellites become apparent, their numbers keep increasing. This is evident at the Space Flight Laboratory (SFL) located at the University of Toronto Institute for Aerospace Studies which has seen a rapid growth in satellite missions in recent years. By leveraging the use of the Generic Nanosatellite Bus developed at SFL, satellites can be rapidly developed to carry science payloads or demonstrate the capabilities of new technologies on orbit. Testing satellite systems in an Earth environment is an important step in qualifying them for space. This thesis describes the development of ground support equipment for testing SFL’s nanosatellite separation system, XPOD, and characterizing the performance of the propulsion system, CNAPS. Also, the thermal behaviour of a pressure regulator valve on CNAPS is examined for various flow conditions.

The BRIght Target Explorer mission consists of six nanosatellites, each equipped with an instrument capable of capturing defocused images of stars suitable for milli-magnitude accuracy differential photometry. BRITE is expected to provide information about the dynamics and life cycles of bright stars. The satellites are funded in pairs by Austria, Poland and Canada and designed at the University of Toronto Institute for Aerospace Studies, Space Flight Laboratory. The present thesis document summarizes the contribution of the author to this project. This includes unit level integration, calibration, functional testing and science acceptance testing of the two BRITE Canada payloads; high level assembly and spacecraft level testing of the BRITE Canada spacecraft; sun stare testing and ground based observations of stars with engineering model instruments; launch campaign functional testing and preparations of UniBRITE, the first BRITE satellite funded by Austria; and on-orbit operations of UniBRITE.

The BRIght Target Explorer mission consists of six nanosatellites, each equipped with an instrument capable of capturing defocused images of stars suitable for milli-magnitude accuracy differential photometry. BRITE is expected to provide information about the dynamics and life cycles of bright stars. The satellites are funded in pairs by Austria, Poland and Canada and designed at the University of Toronto Institute for Aerospace Studies, Space Flight Laboratory. The present thesis document summarizes the contribution of the author to this project. This includes unit level integration, calibration, functional testing and science acceptance testing of the two BRITE Canada payloads; high level assembly and spacecraft level testing of the BRITE Canada spacecraft; sun stare testing and ground based observations of stars with engineering model instruments; launch campaign functional testing and preparations of UniBRITE, the first BRITE satellite funded by Austria; and on-orbit operations of UniBRITE.

Virginia Tech, Utah State University, and the University of Washington were teamed to form the Ionospheric Observation Nanosat Formation to investigate formation-flying requirements for multiple spacecraft missions. A communication subsystem for the mission will comprise an uplink, downlink and a satellite-to-satellite crosslink. A linearly polarized resonant loop antenna mounted above the bottom surface of the spacecraft was selected for a possible satellite uplink receive antenna. The resonant loop was chosen to satisfy the physical requirements of the spacecraft whild still achieving efficient operation for a UHF signal. A full-scale prototype was fabricated to measure frequency dependent characteristics of the antenna. A gamma match and a quarter-wave sleeve balun transformer were integrated to the system to minimize the power reflected at the antenna input and to isolate the antenna from the feed line. The uplink antenna demonstrated sufficient performance; however, the final bandwidth of less than one percent will require additional tuning as other subsystems are integrated into the final flight-ready prototype. / Master of Science

L’environnement spatial est extrêmement agressif, en particulier en raison de la présence de radiations. Ces radiations produisent divers effets, soit cumulatifs soit singuliers qui mettent en péril la fiabilité des satellites. Sur les satellites à budgets contraints, l’utilisation de composant durcis est à proscrire pour des questions de coût. Les composants utilisés sont des composants commerciaux dont la tenue aux radiations n’est généralement pas connue. Sur les satellites scientifiques ou commerciaux, une procédure dite Radiation Hardness Assurance (RHA) est mise en place et vise à réduire les risque en évaluant la sensibilité aux radiations de tous les composants. Afin de garantir le niveau de fiabilité des nanosatellites, nous proposons dans le cadre de cette thèse d’aider au développement d’une RHA spécifique. / Space environment is harsh, especially because of radiations. These radiations induce cumulative and singular effects that can reduce the overall reliability of a satellite. For low-cost space systems, the use of radiation hardened components is prohibited because of their high cost. Commercial components are preferred but their radiation sensitivity is often unknown. Scientific and commercial space projects require a Radiation Hardness Assurance (RHA) process in order to reduce the risk and ensure a better reliability by providing a study at component level. We propose in this thesis the study and development of RHA methods dedicated and tailored for nanosatelittes.

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.

Contributions to two nanosatellite missions are discussed. First, the design and development of a test system for an advanced nanosatellite power board is discussed. Details of software and hardware design process involved in the implementation of automated test procedures are presented. The system has been deployed for unit-level testing of power boards for several nanosatellite missions, significantly reducing testing cost and time. Next, a Mission Planning and Scheduling Software platform is proposed for Earth Observation missions. The motivation is described for the development of a stand-alone application enabling satellite operations teams to identify suitable observation scenario parameters. Attitude and orbital trajectory estimation algorithms constituting the computational model are integrated and implemented within a graphical visualization environment to allow interaction with the user in an efficient and intuitive manner. Key results of major component-level testing are presented, showing the behaviour and accuracy of analytical components satisfy mission requirements.