AIAA S-115-2013 Low Earth Orbit Spacecraft Charging Design Standard Requirement and Associated Handbook.pdf

1、 ANSI/AIAA S-115-2013Standard Low Earth Orbit Spacecraft Charging Design Standard Requirement and Associated Handbook American National Standard AIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 1801 Alexander Bell Drive, Reston, VA 20191-4344 USA. All

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3、oduced in any way. In addition, the electronic file may not be distributed elsewhere over computer networks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. ANSI/AIAA S-115-2013 American National Standard Low Earth Orbit Sp

4、acecraft Charging Design Standard Requirement and Associated Handbook Sponsored by American Institute of Aeronautics and Astronautics Approved September 2013 American National Standards Institute Abstract This standard presents an overview of the current understanding of the various plasma interacti

5、ons that can result when a high-voltage system is operated in the Earths ionosphere, references common design practices that have exacerbated plasma interactions in the past, and recommends standard practices to eliminate or mitigate such reactions. ANSI/AIAA S-115-2013 iii Approval of an American N

6、ational Standard requires verification by ANSI that the requirements for due process, consensus, and other criteria have been met by the standards developer. Consensus is established when, in the judgment of the ANSI Board of Standards Review, substantial agreement has been reached by directly and m

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11、hdraw this standard no later than five years from the date of approval. Purchasers of American National Standards may receive current information on all standards by calling or writing the American National Standards Institute. Published by American Institute of Aeronautics and Astronautics 1801 Ale

12、xander Bell Drive, Reston, VA 20191 Copyright 2013 American Institute of Aeronautics and Astronautics All rights reserved No part of this publication may be reproduced in any form, in an electronic retrieval system or otherwise, without prior written permission of the publisher. Printed in the Unite

13、d States of America ISBN 978-1-62410-246-2 American National Standard ANSI/AIAA S-115-2013 iv Contents Foreword . v Introduction vii Trademarks vii 1 Scope . 1 1.1 Purpose . 1 1.2 Applicability 1 2 Tailoring . 2 3 Applicable Documents . 2 3.1 General 2 3.2 Government and International Documents 2 3.

14、3 Nongovernment Documents 3 3.4 Order of Precedence . 3 4 Vocabulary . 3 4.1 Acronyms and Abbreviated Terms 3 4.2 Terms and Definitions 5 5 Requirements 14 5.1 General LEO Standard Requirements 14 6 Reference Documents Guidance for LEO Spacecraft Charging Design and Test Practices . 18 Annex A Overv

15、iew of Plasma Interactions (Informative) 19 A.1 Poisson Equation . 19 Annex B Environments (Informative) . 20 B.1 The Ambient Environment . 20 Annex C Plasma Interactions (Informative) 23 C.1 Exposed High-Voltage Conductors . 23 C.2 Current Collection 23 C.3 Arcing . 30 Annex D Mitigation Techniques

16、 (Informative) 45 D.1 Current Collection 45 D.2 Controlling Spacecraft Potential 46 D.3 Vented Enclosures 48 D.4 Arcing . 48 ANSI/AIAA S-115-2013 v Annex E Modeling (Informative) . 51 E.1 Spacecraft Charging 51 E.2 Arcing . 52 Annex F Testing (Informative) 53 Annex G Bibliography . 54 Figures C.1 El

17、ectron current versus bias for three solar array blanket materials . 28 C.2 Peak arc current versus capacitance . 31 C.3 Arc r ate versus voltage for standard interconnect cells . 34 C.4 Typical waveform for an a rc . 36 C.5 Sample of flight array from ESA EURECA mission after sustained arcing . 37

18、C.6 Video frame from EOS-AM1 sustained arc test . 38 C.7 Arc site of sustained arc on EOS-AM1 sample array 39 C.8 The end of the remaining TSS-1R tether . 40 C.9 Anodized aluminum plate after repeated arcing 40 C.10 EMI from a small solar array arc and a hypothetical ISS anodized aluminum arc compar

19、ed to Orbiters specifications . 41 D.1 Voltage breakdown of pure gases as a function of pressure times spacing . 46 E.1 An EWB contour plot of ISS potentials 52 Tables 1 Differences between good GEO and LEO design practices . 2 B.1 Nominal properties of ionospheric layers . 21 C.1 Leakage current fr

20、om positively charged solar arrays . 29 ANSI/AIAA S-115-2013 vi Foreword This document is based on the low Earth orbit (LEO) Spacecraft Charging Design Guidelines (Ferguson and Hillard, 2003), and the National Aeronautics and Space Administration (NASA) Low Earth Orbit Spacecraft Charging Design Sta

21、ndard NASA-STD-(I)-4005 (2006) and NASA-STD-4005 and NASA-HDBK-4006 (2007) and has the same authors, Ferguson and Hillard, as those documents. It is the first American National Standard in its subject area and thus does not cancel or replace any other American National Standard in whole or in part.

22、Only minor technical changes and updates distinguish the present standard from NASA-STD-(I)-4005. The present standard deals only with surface charging in LEO environments. In particular, this standard is not intended to replace NASA TP-2361, which is applicable to geosynchronous Earth orbit (GEO) p

23、lasma environments, or NASA-HDBK-4002, which deals only with deep dielectric charging. NASA-HDBK-4002A, which covers only charging environments outside of equatorial LEO and deep-dielectric charging, is also not to be replaced by this document. In this document, all of the Annexes are only informati

24、ve. The only requirements in this standard are in Section 5 (Requirements). At the time of approval, the members of the AIAA Atmospheric and Space Environment Committee on Standards Working Group for Low Earth Orbit were: Henry Garrett, Chair Jet Propulsion Laboratory Michael Bodeau Northrop Grumman

25、 Aerospace Systems Dale Ferguson NASA Marshall Space Flight Center Dale Johnson Retired Justin Likar Lockheed Martin Space Systems Kent Tobiska Space Environment Technologies William Vaughan University of Alabama, Huntsville Albert Whittlesey Jet Propulsion Laboratory John Wise Air Force Research La

26、boratory The above consensus body approved this document in July 2013. The AIAA Standards Executive Council (VP-Standards Laura McGill, Chairperson) accepted the document for publication in August 2013. The AIAA Standards Procedures dictates that all approved standards, recommended practices, and gu

27、ides are advisory only. Their use by anyone engaged in industry or trade is entirely voluntary. There is no agreement to adhere to any AIAA standards publication and no commitment to conform to or be guided by standards reports. In formulating, revising, and approving standards publications, the com

28、mittees on standards will not consider patents that may apply to the subject matter. Prospective users of the publications are responsible for protecting themselves against liability for infringement of patents or copyright, or both. ANSI/AIAA S-115-2013 vii Introduction The purpose of this document

29、 and information handbook is to provide design standard requirements for high-voltage space power systems (55 V) that operate in the plasma environment associated with LEO (altitude between 200 km and 1000 km, and latitude between -50 degrees and +50 degrees). Such power systems, particularly solar

30、arrays, are the proximate cause of spacecraft charging in LEO, and these systems can interact with this environment in a number of ways that are potentially destructive to themselves and to the platform or vehicle that has deployed them. This document is also applicable to satellites during the lowe

31、r latitude portion of polar orbits and to GEO satellites during the initial low altitude portion of their geostationary transfer orbit. This document represents the technical consensus of the spacecraft charging community. Systems designers need a standard to show them how to mitigate the spacecraft

32、 charging effects of using high voltages in LEO. In addition to system designers, this document should be useful to project managers, solar array designers, system engineers, etc. This document is intended as a standard for design applications and can be used as a requirements-specification instrume

33、nt. ANSI/AIAA S-115-2013 viii Trademarks The following commercial products that require trademark designation are mentioned in this document. This information is given for the convenience of users of this document and does not constitute an endorsement. Equivalent products may be used if they can be

34、 shown to lead to the same results. Kapton (a registered trademark of du Pont de Nemours and Company) ANSI/AIAA S-115-2013 1 1 Scope This document and information handbook presents an overview of the current understanding of the various plasma interactions that can result when a high-voltage system

35、is operated in the Earths ionosphere. This document is also applicable to satellites during the lower latitude portion of polar orbits and to GEO satellites during the initial low altitude portion of their geostationary transfer orbit. It references common design practices that have exacerbated plas

36、ma interactions in the past, and recommends standard requirements and practices to eliminate or mitigate such reactions. 1.1 Purpose The purpose of this standard is to provide the requirements for a design standard for high-voltage space power systems (55 V) that operate in the plasma environment as

37、sociated with LEO (altitude between 200 km and 1000 km and latitude between -50 degrees and +50 degrees). Such power systems, particularly solar arrays, are the proximate cause of spacecraft charging in LEO. These systems can interact with this environment in a number of ways that are potentially de

38、structive to themselves and to the platform or vehicle that has deployed them. High-voltage systems are used in space for two reasons. The first is to save launch weight. High-voltage systems are often used as a means to reduce mass and increase efficiencies by reducing power line I2R losses. High-v

39、oltage systems are also used in space because some spacecraft functions require high voltages. For example, electric propulsion uses voltages from about 300 V (Hall thrusters) to about 1000 V (ion thrusters). For low-voltage power systems, conversion of substantial power to high voltages is required

40、 for these spacecraft functions to operate. The weight of the power conversion systems, power management and distribution (PMAD), can be a substantial fraction of the total power system weight in these cases. It is more efficient, and can save weight, if the high-voltage functions can be directly po

41、wered from a high-voltage solar array, for instance. If the high-voltage function is electric propulsion, then we call such a system a direct-drive electric propulsion system. These two reasons and others are causing spacecraft designers and manufacturers to use high voltages more and more. However,

42、 doing so entails risk; in particular, spacecraft charging in LEO, in contrast to that in GEO, is caused by exposed high voltages and can lead to arcing, power drains, power disruptions, and loss of spacecraft coatings. Thus, system designers need a standard to show them how to mitigate the spacecra

43、ft-charging effects of using high voltages in LEO. In addition to system designers, this document should be useful to project managers, solar array designers, system engineers, etc. This document is intended to provide requirements and associated best practices for design applications and can be use

44、d as a requirements-specification instrument. 1.2 Applicability The contents of this document are applicable to high-voltage space power systems that operate in the plasma environment associated with LEO. This standard is intended for space systems that spend the majority of their time at altitudes

45、between 200 km and 1000 km (usually known as LEO applications) and at latitudes between about 50 degrees and +50 degreesthat is, space systems that do not encounter GEO charging conditions, that do not (often) encounter the auroral ovals of electron streams, and that do not fly through the Van Allen

46、 belts. For the extreme radiation protection that is necessary for orbits in the Van Allen belts, exterior spacecraft charging will likely be a secondary concern. However, internal charging will be very important. It is not in the purview of this document to deal with internal charging. Some of the

47、design standards for LEO are at variance with good design practice for GEO spacecraft. If your spacecraft will fly in both LEO and GEO conditions, then be careful to use design solutions that are applicable in both environmental regimes. Table 1 (Ferguson and Brandhorst, 2012) illustrates some of th

48、e differences between good GEO and LEO design practices. ANSI/AIAA S-115-2013 2 Table 1 Differences between good GEO and LEO design practices Good GEO Practices Good LEO Practices Grounded conductive coatings on solar cells. Closely spaced cells with large coverglass overhang. Negatively grounded po

49、wer system. Positively grounded power system. Low inter-string voltages (Ti, the Debye length is given by D = (kTe/4ne2)1/2 = 7.43 x 102 (Te/n)1/2 cm, where k is the Boltzmann constant, Te is the electron temperature in eV, n is the electron density in cm-3, and e is the charge of the electron. Dielectric non-conducting material Dielectric breakdown electrical discharge within a dielectric due to an applied electric field in excess of the dielectric strength of the material ANSI/AIAA S-115-2013 7 Dielectric constant (relative permittivity) pro