Context: Definitive information is what makes enterprises in the contemporary world continuously move up the ladder in today’s world. Hence they need to be always up to date with the latest advancements. A key point in the enterprise structure is Backup and Disaster Recovery, DR system and this has very high scope for development since it can be integrated with a lot of our daily requirements. On account of this, it has a lot of applicability in future for development of technology. Due to this, we have chosen a Fast Moving Consumer Goods Company, FMCG to conduct experimentation on their Backup and DR system. Objectives: In every organization, Backup and DR plays a crucial role in Business Continuity Planning. This work relates to associate backup and recovery plan with an organizational view. And thereby work on its association with Recovery Time Objective, Recovery Point Objective, time taken for backup, time take for recovery and Total Cost of Ownership. Methods: Literature study is the first step to understand present scenario of trending technologies. Hence our understanding led us to conduct an experimental setup where we compared data that was collected in a case study and evaluated its performance of Backup and DR problems that are faced in today’s technology dominated world. Results: In our research, we took various parameters into consideration, which affect performance of an enterprise Backup and DR system. This drove us to assess disk-based and cloud-based Backup and DR plans in the FMCG environment. Conclusions: In conclusion, we summate that even though there have been a lot of theories and research on how Backup and DR is vital, we still lag behind in research work on which the organizations can rely upon to shift towards advanced technologies without risking their competence. With sufficient research on the entrepreneurial environment, we can improve performance enterprises and improve our present knowledge about cloud Backup and DR thereby improving its conventional usage in the present world.

The number of dynamics needed to model the motion between a Chief and Deputy satellites has grown greatly since the introduction of the Hill, Clohessy-Wilshire (HCW) equations of motion were introduced. The models have grown to include various things like perturbations, specifically drag, J2, and solar radiation pressure. Dynamics models have also been developed that use True Anomaly as the independent variable instead of time. A lot of work has been put forth to also include cases where the Chief is in an eccentric orbit. While these models have increased the fidelity of relative dynamics these models become very complicated to implement. That is why the HCW equations remain extremely popular after all these developments. However, their simplicity causes issues when there is In-Track separation between the Chief and Deputy satellites. The error in the dynamics increases as this separation increases which leads to a typical constraint that the separation between the Chief and Deputy needs to be much smaller than the radius of the Chief's orbit. That is where this works starts, by examining into ways to increase the accuracy in the HCW equations as the In-Track separation between the Chief and Deputy grows. In which, this will be done by using a curvilinear coordinate system. Furthermore, a technique of using a Virtual Chief satellite will by employed to allow for the HCW equations to be valid for cases where the Chief is in an eccentric orbit. / Master of Science / There are many different models that are used to model the relative motion between two satellites. These models vary from low to high fidelity in the different types of perturbation and ranges that they can model. These higher fidelity models because very complex to implement and while useful the low fidelity models are still popular, specifically the HCW equations. This thesis works on making the HCW equations valid for a larger range of cases.

The capability to perform rendezvous and proximity operations about space objects is central to the next generation of space situational awareness. The ability to diagnose and respond to spacecraft anomalies is often hampered by the lack of capability to perform inspection or testing on the target vehicle in flight. While some limited ability to perform inspection can be provided by an extensible boom, such as the robotic arms deployed on the space shuttle and space station, a free-flying companion vehicle provides maximum flexibility of movement about the target. Safe and efficient utilization of a companion vehicle requires trajectories capable of minimizing spacecraft resources, e.g., time or fuel, while adhering to complex path and state constraints. This paper develops an efficient solution method capable of handling complex constraints based on a grid search A* algorithm and compares solution results against a state-of-the-art nonlinear optimization method. Trajectories are investigated that include nonlinear constraints, such as complex keep-out-regions and thruster plume impingement, that may be required for inspection of a specific target area in a complex environment. This work is widely applicable and can be expanded to apply to a variety of satellite relative motion trajectory planning problems. / The capability to perform rendezvous and proximity operations about space objects is central to the next generation of space situational awareness. The ability to diagnose and respond to spacecraft anomalies is often hampered by the lack of capability to perform inspection or testing on the target vehicle in flight. While some limited ability to perform inspection can be provided by an extensible boom, such as the robotic arms deployed on the space shuttle and space station, a free-flying companion vehicle provides maximum flexibility of movement about the target. Safe and efficient utilization of a companion vehicle requires trajectories capable of minimizing spacecraft resources, e.g., time or fuel, while adhering to complex path and state constraints. This paper develops an efficient solution method capable of handling complex constraints based on a grid search A* algorithm and compares solution results against a state-of-the-art nonlinear optimization method. Trajectories are investigated that include complex nonlinear constraints, such as complex keep-out-regions and thruster plume impingement, that may be required for inspection of a specific target area in a complex environment. This work is widely applicable and can be expanded to apply to a variety of satellite relative motion trajectory planning problems. / Master of Science / The ability of one satellite to perform actions near a second space satellite or other space object is important for understanding the space environment and accomplishing space mission goals. The development of a method to plan the path that one satellite takes near a second satellite such that fuel usage is minimized and other constraints satisfied is important for accomplishing mission goals. This thesis focuses on developing a fast solution method capable of handling complex constraints that can be applied to plan paths satellite relative motion operations. The solution method developed in this thesis is then compared to an existing solution method to determine the efficiency and accuracy of the method.

This thesis aimed to develop a rendezvous and proximity operation simulation to be tested with physical sensors and hardware, in order to assess the fidelity and performance of low-cost off-the-shelf systems for a hardware-in-the-loop testbed. With the push towards complex autonomous rendezvous missions, a low barrier to entry spacecraft simulator platform allows researchers to test and validate robotics systems, sensors, and algorithms for space applications, without investing in multimillion dollar equipment. This thesis conducted drone flights that followed a representative rendezvous trajectory while collecting lidar data of a target spacecraft model with a lidar sensor affixed to the drone. A relative orbital motion simulation tool was developed to create trajectories of varying orbits and initial conditions, and a representative trajectory was selected for use in drone flights. Two 3D tracking systems, OptiTrack and Vive, were assessed during these flights. OptiTrack is a high-cost state-of-the-art motion capture system that performs pose estimation by tracking reflective markers on a target in the tracking area. Vive is a lower-cost tracking system whose base stations emit lasers for its tracker to detect. Data collection by two lidar types was also assessed during these flights: real lidar data from a physical sensor, and virtual lidar data from a virtual sensor in a virtual environment. Drone flights were therefore performed in these four configurations of tracking system and lidar type, to directly compare the performance of higher-cost configurations with lower-cost configurations. The errors between the tracked drone position time history and the target position time history were analyzed, and the low-cost Vive and real lidar configuration was demonstrated to provide comparable error to the OptiTrack and real lidar configuration because of the dominance of the drone controller error over the tracking system error. In addition, lidar data of a target satellite model was collected by real and virtual lidar sensors during these flights, and point clouds were successfully generated. The resulting point clouds were compared by visualizing the data and noting the characteristics of real lidar data and its error, and how it compared to idealized virtual lidar data of a virtual target satellite model. The resulting real-world data characteristics were found to be modellable which can then be used for more robust simulation development within virtual reality. These results demonstrated that low-cost and open-source hardware and software provide satisfactory results for simulating this kind of spacecraft mission and capturing useful and usable data. / Master of Science / As space missions become more complex, there is a need for lower-cost, more accessible spacecraft simulation platforms that can test and validate hardware and software on the ground for a space-based mission. In this thesis, two position tracking systems and two lidar data collection types were assessed to see if the performance of a low-cost tracking system was comparable to a high-cost tracking system for a space-based simulation. The tracking systems tested were the high-cost state-of-the-art OptiTrack system and the low-cost Vive system. The two types of lidar data collected were real lidar from a physical sensor and virtual lidar from a virtual sensor. These assessments were performed in four configurations, to test each configuration of tracking system and lidar type. First, a simulation tool was developed to simulate the orbital dynamics of a spacecraft that operates in proximity to another spacecraft. After choosing an orbit and initial conditions that represent one such potential mission, the resulting trajectory was uploaded to a drone which acted as a surrogate for a spacecraft, and it flew the uploaded route around a model satellite, collecting lidar data in the process with a lidar sensor affixed to the drone. The tracking systems provided the drone with its position data, and the lidar sensor on the drone collected lidar data of a model satellite as it flew. The data revealed that the low-cost tracking system performance was comparable to the high-cost tracking system because the drone's controller error dominated over the tracking system errors. Additionally, the low-cost drone and physical lidar sensor generated high quality point cloud data that captured the geometry of the target satellite and illustrated the characteristics of real-world lidar data and its errors. These results demonstrated that low-cost and open-source hardware and software provide satisfactory results for simulating this kind of spacecraft mission and capturing useful and usable data.

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This thesis is concerned about Business Continuity Management with the focus on determination of the RTO and RPO parameters. The work is divided into two main parts. The first section briefly describes theoretical issues of Business Continuity Management in conjunction with IT Service Continuity Management. Then there are described various technologies that are currently used to ensure continuity and recovery of IT systems. In conclusion of the theoretical part, the work focuses on the process of Business Impact Analysis. This thesis thus offers a comprehensive view of main principles and benefits that these concepts have for company and how they should be integrated with each other. It provides an overview of various technologies, their link to RTO and RPO parameters and also the definition of steps of disaster recovery procedure. The work also briefly defines the basic procedure for determination of the RTO and RPO parameters, subsequent steps needed to design recovery solutions and analyzes various aspects which need to be considered when defining the parameters of continuity. The second practical part is based on the previous theoretically defined procedure and its aim is to analyze the data acquired during the questionnaire investigation in chosen company to determine the parameters of continuity for the applications in use and then suggest appropriate ways of addressing their backup and recovery. The result of this thesis is therefore a description of the analysis and practical application of methods for setting the parameters for continuity of information systems and the subsequent establishment of necessary measures.