NASA Scientific and Technical Aerospace Reports
NASA Scientific and Technical Aerospace Reports
NASA Scientific and Technical Aerospace Reports
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discharge phenomena were investigated. The results indicated that the propagation time of the discharge generated plasma<br />
between the discharge site <strong>and</strong> the edge of the test coupon is the critical parameter in determining the waveform of the<br />
discharge current.<br />
Author<br />
Solar Arrays; Panels; Spacecraft Configurations; Electric Discharges; Plasmas (Physics)<br />
20040111040 QinetiQ Ltd., Farnborough, UK<br />
Improved Demonstration of Internal Charging Hazards Using the Realistic Electron Environment Facility (REEF)<br />
Ryden, K. A.; Morris, P. A.; Rodgers, D. J.; Bielby, R.; Knight, P. R.; Sorensen, J.; 8th Spacecraft Charging Technology<br />
Conference; March 2004; 12 pp.; In English; See also 20040111031; No Copyright; Avail: CASI; A03, Hardcopy<br />
Experimental ground testing has been carried out to determine whether digital latches can spontaneously change state in<br />
severe (space weather induced) outer-belt environments via the mechanism of internal spacecraft charging/discharging. A new<br />
facility is employed which improves simulations of the charging environment experienced by satellite equipment <strong>and</strong><br />
materials. Results are presented which demonstrate the complete chain of events from environment to circuit anomaly. The<br />
anomaly rate shows dependence on both charging flux <strong>and</strong> circuit board temperature.<br />
Author<br />
Ground Tests; Hazards; Spacecraft Charging; Computerized Simulation; Relativistic Electron Beams; Test Facilities<br />
20040111041 <strong>NASA</strong> Marshall Space Flight Center, Huntsville, AL, USA<br />
Space Environments <strong>and</strong> Effects (SEE) Program: Spacecraft Charging Technology Development Activities<br />
Kauffman, B.; Hardage, D.; Minor, J.; 8th Spacecraft Charging Technology Conference; March 2004; 8 pp.; In English; See<br />
also 20040111031; No Copyright; Avail: CASI; A02, Hardcopy<br />
Reducing size <strong>and</strong> weight of spacecraft, along with dem<strong>and</strong>ing increased performance capabilities, introduces many<br />
uncertainties in the engineering design community on how materials <strong>and</strong> spacecraft systems will perform in space. The<br />
engineering design community is forever behind on obtaining <strong>and</strong> developing new tools <strong>and</strong> guidelines to mitigate the harmful<br />
effects of the space environment. Adding to this complexity is the continued push to use Commercial-off-the-Shelf (COTS)<br />
microelectronics, potential usage of unproven technologies such as large solar sail structures <strong>and</strong> nuclear electric propulsion.<br />
In order to drive down these uncertainties, various programs are working together to avoid duplication, save what resources<br />
are available in this technical area <strong>and</strong> possess a focused agenda to insert these new developments into future mission designs.<br />
This paper will introduce the SEE Program, briefly discuss past <strong>and</strong> currently sponsored spacecraft charging activities <strong>and</strong><br />
possible future endeavors.<br />
Author<br />
Spacecraft Charging; <strong>NASA</strong> Programs; Research <strong>and</strong> Development<br />
20040111042 <strong>Aerospace</strong> Corp., El Segundo, CA, USA<br />
Spacecraft Charging in a Quasi-Static <strong>and</strong> Dynamic Plasma Environment <strong>and</strong> the Scaling Laws for ESD-Induced<br />
Current Transients<br />
Briet, Richard; 8th Spacecraft Charging Technology Conference; March 2004; 14 pp.; In English; See also 20040111031; No<br />
Copyright; Avail: CASI; A03, Hardcopy<br />
The objective of this paper is to present a general expression for predicting characteristics of an electrical pulse from a<br />
surface discharge. Scaling laws are presented for various shapes of the dielectric surface. For many years satellite design<br />
engineers <strong>and</strong> manufacturers used a (square root of (Area))-scaling law to estimate peak current amplitudes from electrostatic<br />
surface discharges (ESDs) on satellites in orbit. Balmain proposed this scaling law (BSL) in 1978. In some applications,<br />
Balmain’s scaling law generates overly conservative design requirements. This paper presents a general expression for the<br />
pulse shape of surface discharges. For a given surface discharge, the peak current depends on the shape of the surface <strong>and</strong> on<br />
the location of the discharge; the pulse duration depends on the longest linear distance from the site of a discharge to an edge<br />
of the surface.<br />
Author<br />
Spacecraft Charging; Scaling Laws; Electric Discharges; Electric Pulses<br />
20040111043 DPL Science, Inc., Saint Lazare, Quebec, Canada<br />
An Educational Multimedia Presentation on the Introduction to Spacecraft Charging<br />
Lin, E.; dePayrebrune, M.; 8th Spacecraft Charging Technology Conference; March 2004; 11 pp.; In English; See also<br />
20040111031; No Copyright; Avail: CASI; A03, Hardcopy<br />
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