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• W2107228367 abstract "Topic: System Engineering) The conceptual design of a satellite system is a very challenging and crucial engineering problem. The author has investigated empirical and analogy models for the conceptual design of the subsystems of a satellite developing a multidisciplinary design process that has been implemented into a software SEM, acronym for System Engineering Module. Module because SEM will be incorporated in a more general astrodynamics software developed by ESA; the name of this software is STA, Space Trajectory Analysis. The objectives of the work are essentially two. The first objective is the identification of a coherent system engineering process for the design of the subsystems of a satellite in a preliminary phase (phase 0/A), which emulates the design process that takes place in the so-called Facilities. Coherent system engineering process means that the order in which the activities have to be performed must be such that each activity has all the inputs available at the moment it is executed. The second objective is to implement the system engineering process within the ESA Space Trajectory Analysis software suite thanks to a user- friendly, all-in-one tool, which guides the user through the entire design process. The subsystems models that are taken into account in the design process are: Power, Attitude Dynamic and Control System (ADCS), Communication, Propulsion, Thermal, Structure, and Data Handling. Furthermore, the missions are evaluated based on some budgets, notably Mass, Power, Thermal, Data rate, Memory, Data link, and Propellant. The models for the conceptual design of spacecraft subsystems are mostly based on relationships that exist between the parameters of related historical missions and the estimated parameters for the new mission to be designed (parametric methods and analogy methods). In order to have some reliable data on which we can base the subsystems preliminary design and to reduce the boundaries of the research, we decided to consider only the Satellites category as target for the SEM. Satellites are the ones for which most data are available in literature, see References section, due to the large number of flown satellite missions to date. SEM has a Graphical User Interface (GUI), which allows the user to interact with the developed mathematical routines. The user can observe what a change of one or more design parameters means for the outputs, as soon as he modifies these parameters. Inputs and outputs are clearly identified, with plainly visible units, and the user will be able to understand what parameters he needs to provide as input, and where to expect the outputs. The presence of hints and tips enhances the quality of the design; the user is guided through the whole design process, and provided with extra information that allows him to better understand the outputs of the analysis, and whether or not his inputs are appropriate for the analysis he is performing. The design process can be seen as the chain of design activities to go from inputs to outputs. The main activities that allow the user to complete the design of a spacecraft with SEM are: Mission Definition, Payload Definition, Launcher Selection, Space Environment, Ground and Atmosphere, Preliminary Design, and Subsystems Design. SEM has been validated. The validation of SEM is mainly aimed to answer the question: Are we building the right software? This means: Is the software, with its outputs, suitable for the conceptual design of a satellite? In order to answer this question, we apply the SEM design process to one of the ESA's CDF (Concurrent Design Facility) missions, currently available on the ESA website. Our objective is to reproduce the main outputs of the CDF report. The mission we choose is HYPER. The results obtained by SEM, estimating the main budgets mentioned before, are within 20% of the results obtained in the CDF. That is quite a good result if we consider that the margins given in the preliminary phases, for the more detailed design of the successive phases, are usually of the same order of magnitude. In conclusion we can say that SEM provides STA with important features that add a cutting edge to the ESA software suite. There is not such a kind of open-source software that allows the design of the subsystems of a satellite. This is very pioneering in the field of the open-source space-related software designed to date. Besides the tips and warnings to the user, the strength of SEM is the idea behind the" @default.
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• W2107228367 date "2009-06-14" @default.
• W2107228367 modified "2023-09-25" @default.
• W2107228367 title "A System Engineering Tool for the Design of Satellite Subsystems" @default.
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• W2107228367 doi "https://doi.org/10.2514/6.2009-6037" @default.
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