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  • 1
    Publication Date: 2011-08-19
    Description: Two general types of remote power controllers (RPC's), which combine the functions of a circuit breaker and a switch, were developed for use in dc aerospace systems. Power-switching devices used in the designs are the gate-turnoff thyristor (GTO) and MOSFET. The RPC's can switch dc voltages to 1200 V and currents to 1000 A. Seven different units were constructed and subjected to laboratory and thermal vacuum testing. Two of these were dual units that switch both positive and negative voltages simultaneously. The RPC's using MOSFET's have slow turnon and turnoff times which limit surge currents and voltage spiking from high di/dt. The GTO's have much faster transition times. All RPC's have programmable overload tripout proportional to I sq T and microsecond tripout for large overloads.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: ESA Proceedings of ESA Sessions at the 16th IEEE Annual Power Electronics Specialists Conference; p 207-216
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  • 2
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    In:  Other Sources
    Publication Date: 2011-08-11
    Description: Complementary symmetry flip-flop and similar transistor micropower digital logic circuit design
    Keywords: ELECTRONICS
    Type: INSTRUMENTS AND CONTROL SYSTEMS
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  • 3
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    In:  Other Sources
    Publication Date: 2011-08-12
    Description: Low power similar transistor logic microcircuits to minimize power drain through gating options
    Keywords: ELECTRONIC EQUIPMENT
    Type: SPACE(AERONAUTICS, VOL. 49, P. 98, 100, 104.
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  • 4
    Publication Date: 2011-08-18
    Description: The feasibility of using rail accelerators for various in-space and to-space propulsion applications was investigated. A 1 meter, 24 sq mm bore accelerator was designed with the goal of demonstrating projectile velocities of 15 km/sec using a peak current of 200 kA. A second rail accelerator, 1 meter long with a 156.25 sq mm bore, was designed with clear polycarbonate sidewalls to permit visual observation of the plasma arc. A study of available diagnostic techniques and their application to the rail accelerator is presented. Specific topics of discussion include the use of interferometry and spectroscopy to examine the plasma armature as well as the use of optical sensors to measure rail displacement during acceleration. Standard diagnostics such as current and voltage measurements are also discussed. Previously announced in STAR as N83-35053
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Magnetics (ISSN 0018-9464); MAG-20; 324-327
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  • 5
    Publication Date: 2016-06-07
    Description: Design details and design goals are given of an instrumentation package to monitor the effects of the environmental charging of spacecraft surfaces on the systems of operational spacecraft.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Proc. of the Spacecraft Charging Technol. Conf.; p 745-751
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  • 6
    Publication Date: 2016-06-07
    Description: A solar array drive system consisting of a solar array drive mechanism and the corresponding solar array drive electronics is being developed. The principal feature of the solar array drive mechanism is its bidirectional capability which enables its use in mechanical redundancy. The solar array drive system is of a widely applicable design. This configuration will be tested to determine its acceptability for generic mission sets. Foremost of the testing to be performed is the testing for extended duration.
    Keywords: MECHANICAL ENGINEERING
    Type: JPL 10th Aerospace Mech. Symp.; p 185-197
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  • 7
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    In:  CASI
    Publication Date: 2019-05-11
    Description: Micropower transistor logic circuits for spaceborne computers
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-TN-D-1462
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  • 8
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    In:  CASI
    Publication Date: 2019-05-24
    Description: Electronic developments in semiconductor circuits - Digital logic circuits
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-TM-X-52013
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  • 9
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    In:  CASI
    Publication Date: 2019-05-23
    Description: Digital logic circuits for space vehicle logic systems for application in nonspace computer systems
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-SP-5022
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  • 10
    Publication Date: 2016-06-07
    Description: A simulation facility was established to determine the response of typical spacecraft materials to the geomagnetic substorm environment and to evaluate instrumentation that will be used to monitor spacecraft system response to this environment. Space environment conditions simulated include the thermal-vacuum conditions of space, solar simulation, geomagnetic substorm electron fluxes and energies, and the low energy plasma environment. Measurements for spacecraft material tests include sample currents, sample surface potentials, and the cumulative number of discharges. Discharge transients are measured by means of current probes and oscilloscopes and are verified by a photomultiplier. Details of this facility and typical operating procedures are presented.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: Proc. of the Spacecraft Charging Technol. Conf.; p 423-430
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