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Design and test hardware for a solar array switching unitThis paper describes the control of a pulse width modulated (PWM) type sequential shunt switching unit (SSU) for spacecraft applications. It is found that the solar cell output capacitance has a significant impact on SSU design. Shorting of this cell capacitance by the PWM switch causes input current surges. These surges are minimized by the use of a series filter inductor. The system with a filter is analyzed for ripple and the control to output-voltage transfer function. Stable closed loop design considerations are discussed. The results are supported by modeling and measurements of loop gain and of closed-loop bus impedance on test hardware for NASA's 120 V Earth Observation System (EOS). The analysis and modeling are also applicable to NASA's 160 V Space Station power system.
Document ID
19930041867
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Patil, A. R.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Cho, B. H.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Sable, D.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Lee, F. C.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: IECEC '92; Proceedings of the 27th Intersociety Energy Conversion Engineering Conference, San Diego, CA, Aug. 3-7, 1992. Vol. 1 (A93-25851 09-44)
Publisher: Society of Automotive Engineers, Inc.
Subject Category
Electronics And Electrical Engineering
Accession Number
93A25864
Funding Number(s)
CONTRACT_GRANT: NAS5-31442
Distribution Limits
Public
Copyright
Other

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