1、BRITISH STANDARD AEROSPACE SERIES BS2G219: 1983 ISO 6858:1982 (Superseding British Standard G219:1975) Specification for General requirements for ground support electrical supplies for aircraft ISO title: Aircraft Ground support electrical supplies General requirements UDC 629.7.08:621.31BS2G219:198
2、3 This British Standard, having been prepared under the directionof the Aerospace Standards Committee, was published under the authority ofthe Board of BSI and comes intoeffect on 30June1983 BSI 08-1999 The following BSI references relate to the work on this standard: Committee reference ACE/41 Draf
3、t for comment 80/73408 DC ISBN 0 580 13301 X Committees responsible for this British Standard This British Standard was published under the direction of the Aerospace Standards Committee ACE/-. Its preparation was entrusted to Technical Committee ACE/41 upon which the following bodies were represent
4、ed: Civil Aviation Authority Electric Cable Makers Confederation Electronic Components Industry Federation Electronic Engineering Association Society of British Aerospace Companies Limited The following bodies were also represented in the drafting of the standard, through subcommittees and panels: C
5、ivil Aviation Authority (Airworthiness Division) Ministry of Defence Amendments issued since publication Amd. No. Date of issue CommentsBS2G219:1983 BSI 08-1999 i Contents Page Committees responsible Inside front cover National foreword ii 1 Scope 1 2 Field of application 1 3 References 1 4 Definiti
6、ons 1 5 Electrical characteristics 1 6 Electrical protection 2 7 Control circuit and supply 3 8 Safety requirements 3 9 Labelling 4 National appendix A Electromagnetic interference 8 National appendix B Voltage wave-form measurements 8 National appendix C Voltage ripple 9 Figure 1 Standard wiring di
7、agram for three-phase a.c. plug and socket 5 Figure 2 Standard wiring diagram for d.c. plug and socket 5 Figure 3 Envelopes for a.c. surges 6 Figure 4 Envelopes for frequency transients on a.c. supplies 6 Figure 5 Envelopes for d.c. surges 7 Figure 6 Diagram of input circuit to oscilloscope 9 Public
8、ations referred to Inside back coverBS2G219:1983 ii BSI 08-1999 National foreword This British Standard, having been prepared under the direction of the Aerospace Standards Committee, is identical with ISO6858:1982 “Aircraft Ground support electrical supplies General requirements”, published by the
9、International Organization for Standardization (ISO). It supersedes BritishStandard G219:1975 which is withdrawn, and takes account of international agreement by Technical Committee ISO/TC20 in relation to the requirements of ground electrical supplies for aircraft. Requirements for electromagnetic
10、interference, referred to in5.3, are given in National appendix A. Terminology and conventions. The text of the International Standard has been approved as suitable for publication as a British Standard without deviation. Some terminology and certain conventions are not identical with those used in
11、British Standards; attention is drawn especially to the following. The comma has been used as a decimal marker. In British Standards it is current practice to use a full point on the baseline as the decimal marker. Wherever the words “International Standard” appear referring to this standard, they s
12、hould be read as British Standard. The Technical Committee has reviewed the provisions of ISO1540 to which reference is made in the text, and has decided that they are acceptable for use in conjunction with this standard. A related British Standard to ISO1540:1977 is British Standard3G100 “General r
13、equirements for equipment for use in aircraft” Part3:1979 “Characteristics of aircraft electrical power supplies”. In particular, attention is drawn to the following specific references: References are made in5.4.4 and5.6.2 to Annex A and8.2 of ISO1540:1977 which have been reproduced in this standar
14、d as National appendix B and National appendix C respectively. Cross-reference International Standard Corresponding British Standard ISO 461:1965 British Standard3G173:1972 Performance and interchangeability requirements for plugs and sockets for ground electrical supply to aircraft (Technically equ
15、ivalent) ISO 1540:1977 British Standard 3G100-3 Figure 2 Figure 2 (Technically equivalent) Figure 3 Figure 3 (Technically equivalent) clause8.3 clause8.2 (Identical) Figure 7 Figure 7 (Technically equivalent)BS2G219:1983 BSI 08-1999 iii Additional information. National appendix A makes reference to
16、BritishStandard 3G100 “General requirements for equipment for use in aircraft” Part4 “Electrical equipment” Section 2 “Electromagnetic interference at radio and audio frequencies”. A British Standard does not purport to include all the necessary provisions of a contract. Users of British Standards a
17、re responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pagesi toiv, pages1to 10, an inside back cover and a back cover. This standard ha
18、s been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover.iv blankBS2G219:1983 BSI 08-1999 1 1 Scope This International Standard specifies electrical output characteristics, and interface requirements, betwee
19、n an aircraft and ground support electrical supplies. Requirements for safety features are included also. The electrical characteristics relate to nominal28V d.c., and115/200V three-phase,400Hz, a.c., outputs measured at the connector. 2 Field of application The ground support electrical supply faci
20、lities covered by this International Standard are intended to supply power to an aircraft. In some cases the facility may also be capable of being used for aircraft engine starting. This International Standard lays down a number of safety features considered essential to protect aircraft in the vici
21、nity of the ground electrical supply facility. Specifically excluded are requirements for ground traffic control purposes, such as towing points, identification and warning lights etc. 3 References ISO 461, Aircraft Connections for ground electrical supplies 1) . ISO 1540, Aerospace Characteristics
22、of aircraft electrical systems. 4 Definitions For the purpose of this International Standard the relevant definitions in ISO1540 and ISO461, together with the following, apply. 4.1 connector the supply cable interface with the aircraft 4.2 facility equipment designed to supply electrical power to an
23、 aircraft on the ground 4.3 rated load maximum continuous output in kilovoltampers for a.c., and maximum continuous current for d.c. 5 Electrical characteristics 5.1 General The combination of the facility and the interconnecting cable shall provide electrical power at the aircraft connector having
24、characteristics generally in accordance with ISO1540 as amended by this specification. The relevant facility specification shall state the appropriate power rating and any special additional characteristics. The a.c. voltage characteristics stated below apply to line-to-neutral quantities: line-to-l
25、ine characteristics should be as a result of line-to-neutral values being as specified. All a.c. voltages are r.m.s. values unless otherwise stated. All d.c. voltages are mean values unless otherwise stated. The facility shall be capable of supplying electrical power having the specified characteris
26、tics under all extreme environmental conditions encountered at the airfield of use. 5.1.1 A.C. power The a.c. power system shall be three-phase, four-wire, star-connected having a nominal voltage of115/200V, a nominal frequency of400Hz and a phase sequence A-B-C. The neutral point shall be connected
27、 in accordance with the circuits shown in Figure 1. 5.1.2 D.C. power The d.c. power system shall be a two wire system having a nominal voltage of28V, the output of which should be connected in accordance with the circuits shown in Figure 2. 5.2 Interface The interconnecting cable shall be terminated
28、 with a ground supply connector complying with the requirements of ISO461. 5.3 Electromagnetic interference The facility shall be tested in accordance with the requirements of the relevant national standard. 5.4 A.C. steady state output characteristics 5.4.1 Voltage regulation The individual and ave
29、rage of the three-phase voltages at the connector shall be within the range112 to118V for all loads including the permitted unbalance (see5.4.2), up to rated load at power factors between0,8 lagging and1,0. 1) At present at the stage of draft. (Revision of ISO461:1965.)BS2G219:1983 2 BSI 08-1999 5.4
30、.2 Voltage unbalance For unbalanced loads up to15% of rated current the maximum difference between individual phase voltages at the connector shall not exceed3V. 5.4.3 Phase displacement For all loads including permitted unbalance (see5.4.2) the displacement between the corresponding zero points on
31、the waveform shall be within the limits118 and122 . 5.4.4 Voltage waveform When loaded as specified in Annex A of ISO1540, the voltage waveform shall be such that: a) the crest factor lies between1,31 and1,51; b) the r.m.s. value of the total harmonic content does not exceed5% of the fundamental r.m
32、.s. voltage; c) no individual harmonic exceeds4% of the fundamental voltage; d) the divergence of corresponding ordinates from those of the equivalent sine wave does not exceed(15,5+5,5cos2F)% of the measured r.m.s. voltage where V psinF is the equation of the equivalent sine wave. 5.4.5 Voltage mod
33、ulation The modulation of phase voltage (including the effects of frequency modulation) shall not exceed3,5V when measured as the peak-to-valley difference between the maximum and minimum peak voltages reached on the modulation envelope over a period of at least1s. Frequency components of the modula
34、tion envelope waveform shall be within the limits shown in Figure2 of ISO1540. 5.4.6 Frequency The frequency of the supply shall be maintained within the limits390Hz and410Hz. 5.4.7 Frequency drift Variation of the controlled frequency level within the limits defined in5.4.6 due to drift shall not e
35、xceed 5Hz and the rate of frequency drift shall not exceed15Hz/min. 5.4.8 Frequency modulation Frequency variations owing to modulation shall be such that the departure from the average frequency lies within the band defined in Figure3 of ISO1540. 5.5 A.C. transient characteristics 5.5.1 Voltage Tra
36、nsient surge voltages, when converted to their equivalent step functions shall be within the limits of Figure 3. The most severe phase transient shall be used in determining conformity with this requirement. NOTEThe definition of equivalent-step-function is given in 8.3 of ISO1540. Limits4 and5 of F
37、igure 3 apply when switching loads from0% up to80% and down to0% of rated load at unity power factor; limits2 and3 apply when switching loads from0% up to150% and down to0%, of rated load at0,6 power factor lagging. 5.5.2 Frequency Frequency transients shall be within the limits of Figure 4. Limits3
38、 and4 of Figure 4 apply when switching loads from0% up to80% and down to0% of rated load at unity power factor; limits1 and2 apply when switching loads from0% up to150% and down to0% of rated load at0,6 power factor lagging. 5.6 D.C. steady state output characteristics 5.6.1 Voltage The voltage at t
39、he connector shall be within the range26 to29V at any load condition up to rated load. When the facility is used for engine starting, the voltage at the connector shall not be less than20V. The maximum current rating for this condition shall be declared. 5.6.2 Voltage ripple The ripple on the d.c. s
40、upply shall be such that the maximum departure from the average d.c. level is less than2V when measured in accordance with the requirements of8.2 of ISO1540. The r.m.s. values of individual cyclic components of the ripple shall not exceed the values shown in Figure7 of ISO1540. 5.7 D.C. transient ch
41、aracteristics Transient surge voltages, when converted to their equivalent step functions, shall be within the limits of Figure 5 for all operations of the aircraft system. The most severe transient shall be used in determining conformity with this requirement. Limits2 and3 apply when switching load
42、s from5% up to85% and down to5% of rated load. Limit4 applies during engine starting. 6 Electrical protection The minimum protection to be provided shall meet the requirements of6.1 and6.2. Means shall be provided for periodic checking of these minimum protection circuits. When a protective circuit
43、has operated the facility shall remain disconnected from the aircraft until manually reset (see8.2).BS2G219:1983 BSI 08-1999 3 6.1 A.C. system protection 6.1.1 Overvoltage A protection system shall be provided which disconnects the facility from the aircraft electrical system before any line-to-neut
44、ral voltage exceeds the limit1 voltage-time curve in Figure 3. 6.1.2 Undervoltage A protection system shall be provided which disconnects the facility from the aircraft electrical system when the average line-to-neutral voltage drops below102V. A time delay of between2s and4s shall be provided to pr
45、event nuisance tripping. Faster tripping is permissible should the voltage fall below70V under fault conditions. 6.1.3 Frequency A protection system shall be provided which disconnects the facility from the aircraft electrical system when the frequency departs from the range370 to430Hz. A time delay
46、 of between2s and7s shall be provided to prevent nuisance tripping. For frequencies below320Hz, the time delay shall be reduced to less than0,5s. 6.1.4 Phase sequence A phase sequence protective system shall be provided which prevents the facility from being connected to the aircraft electrical syst
47、em when the phase rotation of the generated voltage is incorrect. 6.2 D.C. system protection 6.2.1 Overvoltage A protection system shall be provided which disconnects the facility from the aircraft electrical system before the voltage exceeds the limit1 voltage-time curve in Figure 5. 6.2.2 Undervol
48、tage A protection system shall be provided which disconnects the facility from the aircraft electrical system when the voltage drops below20V. A time delay of between2s and4s shall be provided to prevent nuisance tripping. 6.2.3 Reverse polarity A protection system shall be provided which prevents t
49、he facility from being connected to the aircraft if the polarity of the generated voltage is incorrect. 6.2.4 Reverse current A protection system shall be provided which disconnects the facility from the aircraft electrical system if the reverse current exceeds5% of the continuous rating of the facility. In no circumstances shall the aircraft electrical system be permitted to motor the facilitys prime-mover. 7 Control circuit and supply 7.1 Control circuits Unless otherwise required by the relevant specification, the facility shall be capable of
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