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Showing 1 to 12 of 12 for “"Spacecraft Power"”.
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Modeling and analysis of spacecraft power systems
A comprehensive large-scale power system modeling is developed to facilitate the design and analysis of present and future spacecraft power systems. A two-port coupling method is utilized to provide a modularity in model building and analysis of the system. The modular approach allows the model to …
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Analysis and simulation of dynamics of spacecraft power systems
… analyses, of the dynamics of various spacecraft power systems are performed. Systems' dynamics are analyzed for various operating modes, such as the shunt, battery-charge and battery-discharge modes, as well as the transition mode. Computer models using the EASY5 program are developed …
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Simulation of spacecraft power systems using a modular state variable approach
The power requirements for future spacecraft power systems will be on the order of a few hundred kilowatts to a few megawatts. Because of these power levels, a high-voltage, high-power distribution subsystem may be utilized to transmit power from the source to the different loads. Using current …
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Improving particle confinement in inertial electrostatic fusion for spacecraft power and propulsion
Fusion energy is attractive for use in future spacecraft because of improved fuel energy density and reduced radioactivity compared with fission power. Unfortunately, the most promising means of generating fusion power on the ground (Tokamak based reactors like ITER and inertial confinement …
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Modeling and analysis of spacecraft battery charger systems
Large-signal analysis of various spacecraft power systems is performed to predict the bus dynamics in various modes of operation. The large-signal trajectories of the system's operating point are analyzed employing qualitative graphical representation. The analyses are verified through simulation …
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Evolutionary computation based multi-objective design search and optimization of spacecraft electrical power subsystems
Designing a spacecraft electrical power system (SEPS) is a complex and time-consuming engineering task that involves meeting several design objectives under constraints. A conceptual design of a spacecraft power system involves an optimal selection of available technologies for various components, …
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A low ripple bi-directional battery charger/discharger using coupled inductor
There are two important issues about a spacecraft power conversion system: low ripple current flowing through both battery and bus, and bi-directional power flow to and from the battery. This thesis introduces a novel low ripple current bi-directional battery charge/discharge converter using …
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Optimization of spacecraft battery charger/discharger systems
… methodology to facilitate the optimum design of spacecraft power processing systems. Emphasis is placed on the battery charge and discharge systems. A comparison of several battery charge and discharge topologies is presented. Characteristics which effect the overall system performance are …
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Robust preliminary design for multiple gravity assist spacecraft trajectories
The development of a new spacecraft trajectory design method most often occurs because a particular capability does not exist. The invention is usually considered successful so long as it is capable of producing solutions to the problem in question, and thus satisfies a particular design …
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Design of a scalable nano university satellite bus (IlliniSat-2 bus) command and data handling system and power system
… consists of Command and Data Handling system, Power Generation and Distribution system, Attitude Determination and Control system and Radio system. The IlliniSat-2 is required to be capable of operating a nanosatellite from size 1.5U (10x10x17cm) to 6U (10x22.6x36.6cm) and carrying up to three …
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Collimation of deuterium / 3-helium fusion products for advanced spacecraft propulsion and power
… One potential technology class to provide spacecraft propulsion and power systems involve thermonuclear fusion plasma systems. In this class it is well accepted that d-He3 fusion is the most promising of the fuel candidates for spacecraft applications as the 14.7 MeV protons carry up to 80% …