Design of a power management and distribution system for a thermionic-diode powered spacecraft
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National Aeronautics and Space Administration, National Technical Information Service, distributor , [Washington, D.C, Springfield, Va
Power conditioning., Management systems., Thermionic diodes., Solar thermal propulsion., Low earth orbits., High impulse., Geosynchronous orbits., Energy conversion., Specific imp
|Statement||Greg L. Kimnach.|
|Series||NASA technical memorandum -- 107298.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
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Download Design of a power management and distribution system for a thermionic-diode powered spacecraft EPUB
Design of a Power Management and Distribution System for a Thermionic-Diode Powered Spacecraft Greg L. Kimnach Lewis Research Center Cleveland, Ohio Prepared for the 31st Intersociety Energy Conversion Engineering Conference cosponsored by IEEE, AIChE, ANS, SAE, AIAA, and ASME Washington, D.C., AugustNational Aeronautics and Space File Size: KB.
The Electrical Systems Development Branch of the Power Technology Division at the NASA Lewis Research Center in Cleveland, Ohio is designing a Power Management and Distribution (PMAD) System for the Air Force's Integrated Solar Upper Stage (ISUS) Engine Ground Test Demonstration (EGD).
The Electrical Systems Development Branch of the Power Technology Division at the NASA Lewis Research Center in Cleveland, Ohio is designing a Power Management and Distribution (PMAD) System for the Air Force's Integrated Solar Upper Stage (ISUS) Engine Ground Test Demonstration (EGD).Author: Greg L.
Kimnach. Design of a power management and distribution system for a thermionic-diode powered spacecraft Conference Kimnach, G L The Electrical Systems Development Branch of the Power Technology Division at the NASA Lewis Research Center in Cleveland, Ohio is designing a Power Management and Distribution (PMAD) System for the Air Force`s integrated Solar.
To that end, a modular power management and distribution system is proposed which will help transition the aerospace industry towards an assembly line approach to building spacecraft.
The modular system is based on an innovative DC voltage boost converter called the series connected boost unit Author: Robert Button. Power Subsystem Design.
• Identify requirements. – mission lifetime – spacecraft electrical power profile, especially average power. • Select and size power source. – usually solar arrays for Earth-orbiting s/c – EOL requirement, type of Design of a power management and distribution system for a thermionic-diode powered spacecraft book cell, configuration, all drive size.
• Select and size energy Size: KB. limit to the maximum current and power in the clamped reverse voltage region. Also, following the end of forward conduction in any diode, there is reverse current for a short time.
The device does not attain its full blocking capability until the reverse current ceases The second region, at reverse biases more positive than the PIV, has only a veryFile Size: KB.
Spacecraft thermal modelling and testing 3. STC design procedure There is a great variety of actions related to a given spacecraft thermal control project. The traditional steps followed in the thermal design of a spacecraft may be (in chronological order): • Identify your components (at least the most sensitive items) within the overall system.
28 V dc aircraft system voltage was established during WW II era (then sometimes called a 24 volt, or 27 volt or 30 volt system). • In the early s the decision was made to adopt Hz, 3-phase, / volt system as future aircraft electrical power system.
AIRCRAFT ELECTRICAL POWER SYSTEM Author: Neno Novakovic, Milorad Manojlovic. a lower potential. This heat generation may be intended by design, as in any heating appliance (for example, a toaster, an electric space heater, or an electric blanket).
Such an appliance essentially consists of a conductor whose resistance is chosen so as to produce the desired amount of resistive heating. The paper presents the development of the power, propulsion, and thermal systems for a 3U CubeSat orbiting Earth at a radius of km measuring the radiation imbalance using the RAVAN (Radiometer Assessment using Vertically Aligned NanoTubes) payload developed by NASA (National Aeronautics and Space Administration).
The propulsion system was selected as a Mars-Space PPTCUP -Pulsed Cited by: 2. Design of a power management and distribution system for a thermionic-diode powered spacecraft Author: Greg L Kimnach ; Lewis Research Center, ; United States.
Design of a power management and distribution system for a thermionic-diode powered spacecraft (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: Greg L Kimnach; United States.
National Aeronautics and Space Administration. The most common electrical-power-generation system for spacecraft is the combination of solar-photovoltaic arrays and batteries as shown schematically in the following figure, Figure Photovoltaic- battery system (Patel).
PMAD = power management and distribution PRU = power regulation unit BAT = batteries EPS = electrical power system =File Size: 1MB.
The principle of power system analysis by V. Mehta is best of best book ever written on power system transmission and distribution. In most of the engineering universities the edition the is used for study is 4 th as it included some extra chapter than older ones.
The little book contains basic information of power system. Design of a power management and distribution system for a thermionic-diode powered spacecraftAuthor: Robert Button.
Pathfinder spacecraft, which used only solar and battery power, operated only three months. • They are lightweight and compact. In the kilowatt range, RTGs provide more power for less mass (when compared to solar arrays and batteries). • No moving parts or fluids, conventional RTGs highly reliable.
• RTGs are safe and flight-proven. Spacecraft Power Systems. The power systems of space vehicles have undergone significant development during the previous decade, and will continue to do so in the immediate future.
Details Design of a power management and distribution system for a thermionic-diode powered spacecraft EPUB
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.5/5(2).
power electronic interface (APEI) that is scalable to meet different power requirements, with modular design, lower cost, and improved reliability, will improve the overall cost and durability of distributed and renewable energy systems.
This report presents a summary providing a. Requirements for Space Systems), and MIL-STD (Electrical Power, Direct Current, Space Vehicle Design Requirements) together comprise a fairly complete set of requirements, but they were written so long ago that they are difficult to apply to many of today’s design practices.
This comparative study of electric power distribution systems for spacecraft concentrates on two interrelated issues: (1) the choice between dc and high-frequency ac, and (2) the converter/inverter topology to be used at the power source.
The report opens first with a discussion of the relative merits of dc and ac : Thomas A. Stuart, Roger J. King. In Chapter 7, the design methodology of series hybrid electric drive trains is presented. This chapter focuses on the power design of engine and energy storage, design of traction motor, transmission characteristics, and control strategy.
A design example is also provided. In Chapter 8, the design methodology of parallel hybrid electric driveFile Size: 8MB. Qualitative Event-based Diagnosis with Possible Conflicts Applied to Spacecraft Power Distribution Systems M. Daigle, A. Bregon, and I.
Roychoudhury, Proceedings of the 8th IFAC Symposium on Fault Detection, Supervision and Safety of Technical Processes, Mexico City, Mexico,August Trailblazing Resources to Optimize Design and Application.
Thermal Hydraulics for Space Power, Propulsion, and Thermal Management System Design (Progress in Astronautics & Aeronautics) [Krotiuk, William J.] on *FREE* shipping on qualifying offers. Thermal Hydraulics for Space Power, Propulsion, and Thermal Management System Design (Progress in Astronautics & Aeronautics)Cited by: 4.
The electrical power subsystem provides electrical energy sources, power generation and control, power conversion and conditioning, and power distribution to the spacecraft throughout the mis sion. For checkout before launch, de electrical power is supplied by ground support equipment.
The electrical power subsystem furnishes drinking. Zhang and C. Mi, Vehicle Power Management, Power Systems, DOI: /_1, Springer-Verlag London Limited 1 2 1 Introduction barrels in. The voltage and current of electrical power available on any particular spacecraft will be dictated by the power source and the power management and distribution architecture.
Various payloads will then most likely require the power in a different form, such as higher voltage for electric propulsion. The electrical system of the International Space Station is a critical resource for the International Space Station (ISS) because it allows the crew to live comfortably, to safely operate the station, and to perform scientific experiments.
The ISS electrical system uses solar cells to directly convert sunlight to numbers of cells are assembled in arrays to produce high power. 8th IFAC Symposium on Fault Detection, Supervision and Safety of Technical Processes (SAFEPROCESS) AugustMexico City, Mexico Fault Isolation for Spacecraft Systems: An Application to a Power Distribution Testbed Joshua D.
Carl Daniel L.C.
Description Design of a power management and distribution system for a thermionic-diode powered spacecraft FB2
Mack Ashraf Tantawy Gautam Biswas Xenofon D. Koutsoukos Institute for Software Integrated Systems, Vanderbilt University, Cited by: 1. The research reported in this dissertation focuses on the development of optimization tools for the design of subsystems in a modern aircraft power distribution system.
The baseline power distribution system is built around a V DC bus. One of the distinguishing features of this power distribution system is the presence of regenerative power.The INSIDE Jupiter spacecraft is solar powered and carries no nuclear powered components.
Design features include extensive use of flight heritage components, full redundancy, radiation hard electronics, dual use structural components, and an integrated thermal design. Fig. 4 shows the deployed spacecraft as configured in Jupiter by: 1.4 Spacecraft Electric Power BACKGROUND AND STATUS A spacecraft's electrical power system generally consists of the primary power generating unit (solar or nuclear), the power management and distribution system, and an energy storage unit.
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