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The power systems of space vehicles have undergone significant development during the previous decade, and will continue to do so in the immediate future. Until now, except for the scattered results of conferences and a few publications with sketchy coverage, no single volume has covered the entire spectrum of the subject. Spacecraft Power Systems addresses every facet of electrical power system design, analyses, and operation with a level of detail found nowhere else. The book delivers wide coverage of the fundamentals of energy conversion, energy storage, power conditioning, energy management, and operational aspects that help engineers maintain a leading edge in the design of various systems. This volume provides the most recent data and procedures for designing an electrical power system that meets mission requirements at a minimum of cost and weight. This book evolved from courses taught by the author and from the author's deep involvement in many design and development programs at the General Electric Space Division and at Lockheed Martin Space Systems.
As a stand-alone volume, Transistor Circuits For Spacecraft Power System presents numerous transistor circuits and building blocks associated with power electronics in general, and examines the major subsystem components for solar-based spacecraft power systems. The technique and concept, of "continuity of states" for nonlinear circuits handling power transfer under cyclic excitation is introduced in Part I and further developed throughout the book. This powerful technique employing matrix formulation bypasses eigen-transients and yields steady-state responses rapidly. Closed-loop treatments are also given for large-scale linear circuits, many closed-form solutions for control loop-gain, conducted susceptibility, output impedance, etc. are covered. Extensive mathematical procedures are retained to highlight the importance of analytical flows. The author also reviews the evolution of solar-based spacecraft power systems; introduces modes of operations: discharge (boost), shunt, and charge; and covers pulse-width-modulated (PWM) boost power converter for both DC and AC conditions. A configuration tree for shunt mode operation is conceived. Based on the configuration tree, the best topologies, sequential PWM shunt and ripple-regulated free-running shunt, are intensively examined and formulated. Transistor Circuits For Spacecraft Power System provides important information for understanding the relationship between earthbound semiconductor circuits and space borne vehicles.
This document, when followed in its entirety, will yield a robust EPS design suitable for very high-reliability space missions. This document specifies general design practices and sets minimum verification and validation requirements for power systems of unmanned spacecraft. The focus of the document is on earth orbiting satellites using traditional photovoltaic/battery power, but does not exclude other primary power generation and storage methods. This document does not address specific launch vehicle requirements however much of the design philosophy used here is applicable to launch vehicle power systems.
Spacecraft require electrical energy. This energy must be available in the outer reaches of the solar system where sunlight is very faint. It must be available through lunar nights that last for 14 days, through long periods of dark and cold at the higher latitudes on Mars, and in high-radiation fields such as those around Jupiter. Radioisotope power systems (RPSs) are the only available power source that can operate unconstrained in these environments for the long periods of time needed to accomplish many missions, and plutonium-238 (238Pu) is the only practical isotope for fueling them. Plutonium-238 does not occur in nature. The committee does not believe that there is any additional 238Pu (or any operational 238Pu production facilities) available anywhere in the world.The total amount of 238Pu available for NASA is fixed, and essentially all of it is already dedicated to support several pending missions--the Mars Science Laboratory, Discovery 12, the Outer Planets Flagship 1 (OPF 1), and (perhaps) a small number of additional missions with a very small demand for 238Pu. If the status quo persists, the United States will not be able to provide RPSs for any subsequent missions.
Annotation This text discusses the conceptual stages of mission design, systems engineering, and orbital mechanics, providing a basis for understanding the design process for different components and functions of a spacecraft. Coverage includes propulsion and power systems, structures, attitude control, thermal control, command and data systems, and telecommunications. Worked examples and exercises are included, in addition to appendices on acronyms and abbreviations and spacecraft design data. The book can be used for self-study or for a course in spacecraft design. Brown directed the team that produced the Magellan spacecraft, and has taught spacecraft design at the University of Colorado. Annotation c. Book News, Inc., Portland, OR (booknews.com).

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