1、BRITISH STANDARD BS EN2282:1992Characteristics of aircraft electrical suppliesThe European Standard EN 2282:1992 has the status of a British StandardBSEN2282:1992This British Standard, having been prepared under the directionof the Aerospace Standards Policy Committee, waspublished under the authori
2、tyof the Standards Boardand comes into effect on 1May1992 BSI 07-1999The following BSI references relate to the work on this standard:Committee reference ACE/6Draft for comment 90/78663 DCISBN 0 580 20823 0Cooperating organizationsThe European Committee for Standardization (CEN), under whose supervi
3、sion this European Standard was prepared, comprises the national standards organizations of the following countries.Austria Oesterreichisches NormungsinstitutBelgium Institut belge de normalisationDenmark Dansk StandardiseringsraadFinland Suomen Standardisoimisliito, r.y.France Association franaise
4、de normalisationGermany Deutsches Institut fr Normung e.V.Greece Hellenic Organization for StandardizationIceland Technological Institute of IcelandIreland National Standards Authority of IrelandItaly Ente Nazionale Italiano di UnificazioneLuxembourg Inspection du Travail et des MinesNetherlands Ned
5、erlands Normalisatie-instituutNorway Norges StandardiseringsforbundPortugal Instituto Portugus da QualidadeSpain Asociacin Espaola de Normalizacin y CertificacinSweden Standardiseringskommissionen i SverigeSwitzerland Association suisse de normalisationUnited Kingdom British Standards InstitutionAme
6、ndments issued since publicationAmd. No. Date CommentsBSEN2282:1992 BSI 07-1999 iContentsPageCooperating organizations Inside front coverNational foreword iiForeword 2Text of EN 2282 3National annex NA (informative) Committes responsible Inside back coverNational annex NB (informative) Cross-referen
7、ce Inside back coverBSEN2282:1992ii BSI 07-1999National forewordThis British Standard has been prepared under the direction of the Aerospace Standards Policy Committee and is the English language version of EN2282:1992, “Aerospace series. Characteristics of aircraft electrical supplies”, published b
8、y the European Committee for Standardization (CEN).EN 2282 was produced as a result of international discussions in which the United Kingdom took an active part.A British Standard does not purport to include all the necessary provisions of a contract. Users of British Standards are responsible for t
9、heir correct application.Compliance with a British Standard does not of itself confer immunity from legal obligations.Summary of pagesThis document comprises a front cover, an inside front cover, pages i and ii, theEN title page, pages 2 to 20, an inside back cover and a back cover.This standard has
10、 been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover.EUROPEAN STANDARDNORME EUROPENNEEUROPISCHE NORMEN 2282February 1992UDC: 629.7.064.5.621.311.012Key words: Aerospace industry, aircraft, aircraft equipm
11、ent, electrical installation, electrical supply, electrical system, specificationEnglish versionAerospace series Characteristics of aircraft electrical suppliesSrie arospatiale Caractristiques de lalimentation lectrique des aronefsLuft- und Raumfahrt Eigenschaften der elektrischen Stromversorgung vo
12、n LuftfahrzeugenThis European Standard was accepted by CEN on 1991-05-07. CEN membersare bound to comply with the requirements of CEN Internal Regulations whichstipulate the conditions for giving this European Standard the status of anational standard without any alteration.Up-to-date lists and bibl
13、iographical references concerning such nationalstandards may be obtained on application to the CEN Central Secretariat or toany CEN member.This European Standard exists in three official versions (English, French,German). A version in any other language made by translation under theresponsibility of
14、 a CEN member into its own language and notified to CENCentral Secretariat has the same status as the official versions.CEN members are the national standards organizations of Austria, Belgium,Denmark, Finland, France, Germany, Greece, Iceland, Ireland, Italy,Luxemburg, Netherlands, Norway, Portugal
15、, Spain, Sweden, Switzerland andUnitedKingdom.CENEuropean Committee for StandardizationComit Europen de NormalisationEuropisches Komitee fr NormungCentral Secretariat: rue de Stassart 36, B-1050 Brussels CEN 1991 Copyright reserved to all CEN membersRef. Nr EN 2282:1991 EEN2282:1992 BSI 07-19992Fore
16、wordThis European Standard has been prepared by the European Association of Aerospace Manufacturers (AECMA).After inquiries and votes carried out in accordance with the rules of this Association, this Standard has successively received the approval of the National Associations and the Official Servi
17、ces of the member countries of AECMA, prior to its presentation to CEN.According to the Common CEN/CENELEC Rules, the following countries are bound to implement this European Standard:Austria, Belgium, Denmark, Finland, France, Germany, Greece, Iceland, Ireland, Italy, Luxembourg, Netherlands, Norwa
18、y, Portugal, Spain, Sweden, Switzerland and UnitedKingdom.ContentsPageForeword 20 Introduction 31 Scope and field of application 32 References 33 Definitions 34 Requirements common to all on-board systems 55 A.C. power system, 115/200 V 400 Hz 86 D.C. power systems, 28 V 107 Special systems 12Annex
19、A Test method for voltage spikes generated by equipment 19Figure 1 Diagram of designation and rotation of phases Three-phase a.c. power systems 13Figure 2 Characteristics of a.c. frequency modulation 13Figure 3 Envelopes of frequency transients on 400 Hz power systems 14Figure 4 Unbalance limits bet
20、ween phases for equipment using three-phase a.c. power supply 15Figure 5 Power factor limits of any equipment using a.c. power supply 15Figure 6 Envelopes of voltage transients on a.c. systems, 115/200 V 400 Hz 16Figure 7 Envelopes of voltage transients on 28 V d.c. systems 17Figure 8 Limits of comp
21、onents of voltage modulations 18Table 1 Spikes 6Table 2 10Table 3 12Table 4 19Table 5 19EN2282:1992 BSI 07-1999 30 IntroductionThis standard has taken into consideration national documents together with ISO1540 and STANAG3456.1 Scope and field of applicationThis standard specifies the characteristic
22、s of electrical power supplied to the terminals of equipment installed in the aircraft.It also defines the supply systems and compatibility requirements for equipment together with the special systems with constant and variable frequency.This standard applies to a.c. and d.c. on-board or ground syst
23、ems.2 ReferencesISO 1540, Aerospace Characteristics of aircraft electrical systems. ISO 7137, Aircraft Environmental conditions and test procedures for airborne equipment. EN 3371, Aerospace series Bonding1). STANAG 3456, Aircraft electrical system characteristics2). STANAG 3516, Electromagnetic com
24、patibility for aircraft electrical and electronic equipment2). MIL-STD-461, Electromagnetic emission and susceptibility requirements for the control of electromagnetic interference3). 3 Definitions3.1 definition documentstandards or document giving the technical definition of equipment3.2 electrical
25、 system (system)an assembly constitued by the sources of electrical power, utilization equipment, safety devices and all common connections of the installation3.3 power sourcesthey supply the power from one of the aircraft propulsion engines, a power conversion device, a ground support unit, or batt
26、eries3.4 available power of a systemthe power which can be used simultaneously under continuous steady-state conditions taking account of the specified conditions of use in the aircraft and the rated power of each power source3.5 utilization equipmentany equipment or any functional group of units co
27、nsuming electrical energy3.6 normal operationthis covers all the conditions of a system in which the utilization equipment shall retain its performance during the missions intended for the aircraft1) In preparation at the date of publication of the present standard.2) This standard is published by:
28、NATO, Military Agency for Standardization (MAS), B-1110 BRUSSELS.3) This specification is published by: Department of Defense (DOD), the Pentagon, WASHINGTON, D.C.20301.EN2282:19924 BSI 07-1999a distinction shall be made: normal frequent operation, i.e. usual systematic operating conditions (steady-
29、state or transient).Examples: variations in speed of aircraft engines and/or load of system supply from the ground.Start-up procedures are at the limit of this type of operation. normal rare operation, which may occur randomly a limited number of times in the equipment life.Examples: anomalies of lo
30、ad or control, transfer or paralleling of sources, normal clearing of certain faults and switching of load or engine, more significant than normal frequent .3.7 emergency operationthe condition of the portion of the electrical system remaining in service when the main power sources can no longer res
31、pond to requirementsemergency sources then used are accumulator batteries, converters or generators of limited power (not considered to be utilization equipment)3.8 abnormal operationthe consequence of a failure or disturbance bringing about the loss or deterioration of the system characteristics wh
32、ich may then attain the limits provided by the protective devicesthe extend and duration of this abnormal operation may escape inspection until the end of the flight3.9 steady-state conditionsoperating conditions of the system when only negligible changes in electrical parameters appear which are no
33、t due to any variation in load or any fault3.10 voltage valuesthe value of the a.c. voltage is defined by the r.m.s. value measured between each phase and the neutral, the value of the d.c. voltage is defined by the mean arithmetical value measured between the positive terminal and earth3.11 transie
34、ntsmomentary variations of a characteristic from its steady-state conditions. They result, for example, from the response of the generator regulator to a disturbancebrief undervoltages or interruptions due to switching, may be considered as transients3.12 spikesbrief variations, also called voltage
35、peaks, compared with steady-state conditions or transients which arise in the distribution system, for example, from switching of inductive loadsthey generally produce a voltage peak and/or a wave train, the characteristics of which are dependent on relative impedances of the line, equipment and pow
36、er source, and on the manner in which the interruption occurs3.13 driftthis is a random and extremely slow variation in a controlled parameter inside the specified limitsthe speed of variation or drift rate of the parameter is expressed inHz/min or inV/min3.14 modulationsthe modulation of the parame
37、ter is the cyclic (generally non-sinusoidal) or random variation of its maximum value around a mean value in steady-state conditionsfor a.c. power, the maximum value of modulation (of voltage or current) is the maximum difference between the peak values of the parameter measured on the most unfavour
38、able phase and polarityEN2282:1992 BSI 07-1999 5for d.c. power, it is called ripple its value is the difference between the mean value (of voltage or current) and the maximum or minimum value attained, measured on either side of the mean valuein both cases, modulation may be likened to the superimpo
39、sition of an alternating wave on the base parametera harmonic analysis 4) of this wave or of its envelope indicates the frequencies and amplitudes of its components, with a view to limiting them (seeFigure 8)3.15 frequency variationsduring transients or modulations of frequency, the instantaneous va
40、lue of the frequencyf of a non-periodic wave is deduced from the intervalt between two consecutive passages of the wave to zero, by the formula:its speed (or rate) of variation is expressed in Hz/sthe frequency, or rate of repetition, of the frequency modulation is expressed in the number of occurre
41、nces (or periods) per second or minute3.16 total harmonic content (current or voltage)the percentage of distortion (harmonics, modulation, etc.) compared with the sinusoidal basic waveit measures the ratio of the r.m.s. value of the total wave, reduced by the fundamental component, to the r.m.s. val
42、ue of the fundamental periodic wave3.17 individual harmonic contentthe ratio between the r.m.s. value of the fundamental component and the r.m.s. value of the fundamental periodic wavethe harmonic analysis4) or spectrum of distortion decomposes a periodic wave giving the amplitude of its components
43、depending upon their frequency4 Requirements common to all on-board systems4.1 General conditions for power generationThe requirements applicable to the systems shall permit them to provide the types of operation in the conditions of use described and within the limits of the envelopes ofFigure 6 an
44、dFigure 7.Except where specified otherwise (e.g.nominal voltages), all the values of parameters specified in this standard shall be measured at the equipment terminals including during the power supply to the aircraft by a ground support unit, in conformity with this standard.NOTEin case of specific
45、 applications or necessity it may also be beneficial to increase or reduce the severity of the required characteristics for generators and systems. In this case the limit values of the parameters shall be the subject of an agreement between the interested parties, have the approval of the official S
46、ervices and be specified in the particular specifications.4.1.1 Supplied powerIn continuous steady-state conditions the power consumed on the system shall be between5% and85% of the available power.In transient conditions the power to be switched shall be compatible with the generator regulation.Exa
47、mples: in normal frequent operation, establishment and cut-off from5% to85% of rated power of the source or sources, in normal rare operation this percentage may go from0% to170% (if applicable to the system overload capacity).4) Decomposition into Fourier series .f 12t-=EN2282:19926 BSI 07-19994.1.
48、2 Operating selectivityThe behaviour of the regulation and the selectivity of the protective devices (primary and secondary) shall be such that: no single failure on the distribution system shall cause deterioration of the normal operation of the generators, nor that of the utilization equipment not
49、 involved by this failure; the isolation of a fault having caused abnormal operation shall not have any effect on the other systems except a possible transient.4.1.3 InterruptionsThe duration of power interruptions which may occur in flight and on the ground in the case of transfer of sources shall not exceed50ms, except where specified otherwise, in this case they shall not exceed150ms.The specification for each system or aircraft shall state the duration of these interruptions (wave
