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1、BRITISH STANDARD BS EN 2282:1992 Characteristics of aircraft electrical supplies The European Standard EN 2282:1992 has the status of a British Standard Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI BS EN 2282:1992 This British Standard, h
2、aving been prepared under the direction of the Aerospace Standards Policy Committee, was published under the authority of the Standards Board and comes into effect on 1 May 1992 BSI 07-1999 The following BSI references relate to the work on this standard: Committee reference ACE/6 Draft for comment
3、90/78663 DC ISBN 0 580 20823 0 Cooperating organizations The European Committee for Standardization (CEN), under whose supervision this European Standard was prepared, comprises the national standards organizations of the following countries. AustriaOesterreichisches Normungsinstitut BelgiumInstitut
4、 belge de normalisation DenmarkDansk Standardiseringsraad FinlandSuomen Standardisoimisliito, r.y. FranceAssociation franaise de normalisation GermanyDeutsches Institut fr Normung e.V. GreeceHellenic Organization for Standardization IcelandTechnological Institute of Iceland IrelandNational Standards
5、 Authority of Ireland ItalyEnte Nazionale Italiano di Unificazione LuxembourgInspection du Travail et des Mines NetherlandsNederlands Normalisatie-instituut NorwayNorges Standardiseringsforbund PortugalInstituto Portugus da Qualidade SpainAsociacin Espaola de Normalizacin y Certificacin SwedenStanda
6、rdiseringskommissionen i Sverige SwitzerlandAssociation suisse de normalisation United KingdomBritish Standards Institution Amendments issued since publication Amd. No.DateComments Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI BS EN 2282:1
7、992 BSI 07-1999i Contents Page Cooperating organizations Inside front cover National foreword ii Foreword 2 Text of EN 2282 3 National annex NA (informative) Committes responsibleInside back cover National annex NB (informative) Cross-reference Inside back cover Licensed Copy: sheffieldun sheffieldu
8、n, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI BS EN 2282:1992 ii BSI 07-1999 National foreword This British Standard has been prepared under the direction of the Aerospace Standards Policy Committee and is the English language version of EN 2282:1992, “Aerospace series. Chara
9、cteristics of aircraft electrical supplies”, published by 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
10、contract. Users of British Standards are 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, pages i and ii, the EN title page, pages 2
11、to 20, an inside back cover and a back cover. This standard has been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover. Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontr
12、olled Copy, (c) BSI EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 2282 February 1992 UDC: 629.7.064.5.621.311.012 Key words: Aerospace industry, aircraft, aircraft equipment, electrical installation, electrical supply, electrical system, specification English version Aerospace series Characte
13、ristics of aircraft electrical supplies Srie arospatiale Caractristiques de lalimentation lectrique des aronefs Luft- und Raumfahrt Eigenschaften der elektrischen Stromversorgung von Luftfahrzeugen This European Standard was accepted by CEN on 1991-05-07. CEN members are bound to comply with the req
14、uirements of CEN Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the CEN Central Secret
15、ariat or to any CEN member. This European Standard exists in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to CEN Central Secretariat has the same status as the offici
16、al versions. CEN members are the national standards organizations of Austria, Belgium, Denmark, Finland, France, Germany, Greece, Iceland, Ireland, Italy, Luxemburg, Netherlands, Norway, Portugal, Spain, Sweden, Switzerland and United Kingdom. CEN European Committee for Standardization Comit Europen
17、 de Normalisation Europisches Komitee fr Normung Central Secretariat: rue de Stassart 36, B-1050 Brussels CEN 1991 Copyright reserved to all CEN members Ref. Nr EN 2282:1991 E Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI EN 2282:1992 BSI
18、07-1999 2 Foreword This 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 th
19、e Official Services 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,
20、Netherlands, Norway, Portugal, Spain, Sweden, Switzerland and United Kingdom. Contents Page Foreword 2 0Introduction 3 1Scope and field of application3 2References3 3Definitions3 4Requirements common to all on-board systems5 5A.C. power system, 115/200 V 400 Hz8 6D.C. power systems, 28 V10 7Special
21、systems12 Annex A Test method for voltage spikes generated by equipment19 Figure 1 Diagram of designation and rotation of phases Three-phase a.c. power systems13 Figure 2 Characteristics of a.c. frequency modulation13 Figure 3 Envelopes of frequency transients on 400 Hz power systems14 Figure 4 Unba
22、lance limits between phases for equipment using three-phase a.c. power supply15 Figure 5 Power factor limits of any equipment using a.c. power supply15 Figure 6 Envelopes of voltage transients on a.c. systems, 115/200 V 400 Hz16 Figure 7 Envelopes of voltage transients on 28 V d.c. systems17 Figure
23、8 Limits of components of voltage modulations18 Table 1 Spikes6 Table 210 Table 312 Table 419 Table 519 Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI EN 2282:1992 BSI 07-19993 0 Introduction This standard has taken into consideration natio
24、nal documents together with ISO 1540 and STANAG 3456. 1 Scope and field of application This standard specifies the characteristics of electrical power supplied to the terminals of equipment installed in the aircraft. It also defines the supply systems and compatibility requirements for equipment tog
25、ether with the special systems with constant and variable frequency. This standard applies to a.c. and d.c. on-board or ground systems. 2 References ISO 1540, Aerospace Characteristics of aircraft electrical systems. ISO 7137, Aircraft Environmental conditions and test procedures for airborne equipm
26、ent. EN 3371, Aerospace series Bonding1). STANAG 3456, Aircraft electrical system characteristics2). STANAG 3516, Electromagnetic compatibility for aircraft electrical and electronic equipment2). MIL-STD-461, Electromagnetic emission and susceptibility requirements for the control of electromagnetic
27、 interference3). 3 Definitions 3.1 definition document standards or document giving the technical definition of equipment 3.2 electrical system (system) an assembly constitued by the sources of electrical power, utilization equipment, safety devices and all common connections of the installation 3.3
28、 power sources they supply the power from one of the aircraft propulsion engines, a power conversion device, a ground support unit, or batteries 3.4 available power of a system the power which can be used simultaneously under continuous steady-state conditions taking account of the specified conditi
29、ons of use in the aircraft and the rated power of each power source 3.5 utilization equipment any equipment or any functional group of units consuming electrical energy 3.6 normal operation this covers all the conditions of a system in which the utilization equipment shall retain its performance dur
30、ing the missions intended for the aircraft 1) In preparation at the date of publication of the present standard. 2) This standard is published by: NATO, Military Agency for Standardization (MAS), B-1110 BRUSSELS. 3) This specification is published by: Department of Defense (DOD), the Pentagon, WASHI
31、NGTON, D.C. 20301. Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI EN 2282:1992 4 BSI 07-1999 a distinction shall be made: normal frequent operation, i.e. usual systematic operating conditions (steady-state or transient). Examples: variation
32、s 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 load or control, transfer or parallelin
33、g of sources, normal clearing of certain faults and switching of load or engine, more significant than normal frequent . 3.7 emergency operation the condition of the portion of the electrical system remaining in service when the main power sources can no longer respond to requirements emergency sour
34、ces then used are accumulator batteries, converters or generators of limited power (not considered to be utilization equipment) 3.8 abnormal operation the consequence of a failure or disturbance bringing about the loss or deterioration of the system characteristics which may then attain the limits p
35、rovided by the protective devices the extend and duration of this abnormal operation may escape inspection until the end of the flight 3.9 steady-state conditions operating conditions of the system when only negligible changes in electrical parameters appear which are not due to any variation in loa
36、d or any fault 3.10 voltage values the 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 earth 3.11 transients momentary variations o
37、f a characteristic from its steady-state conditions. They result, for example, from the response of the generator regulator to a disturbance brief undervoltages or interruptions due to switching, may be considered as transients 3.12 spikes brief variations, also called voltage peaks, compared with s
38、teady-state conditions or transients which arise in the distribution system, for example, from switching of inductive loads they generally produce a voltage peak and/or a wave train, the characteristics of which are dependent on relative impedances of the line, equipment and power source, and on the
39、 manner in which the interruption occurs 3.13 drift this is a random and extremely slow variation in a controlled parameter inside the specified limits the speed of variation or drift rate of the parameter is expressed in Hz/min or in V/min 3.14 modulations the modulation of the parameter is the cyc
40、lic (generally non-sinusoidal) or random variation of its maximum value around a mean value in steady-state conditions for 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 unfavourable phase an
41、d polarity Licensed Copy: sheffieldun sheffieldun, na, Thu Nov 02 17:55:23 GMT+00:00 2006, Uncontrolled Copy, (c) BSI EN 2282:1992 BSI 07-19995 for 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, me
42、asured on either side of the mean value in both cases, modulation may be likened to the superimposition of an alternating wave on the base parameter a harmonic analysis 4) of this wave or of its envelope indicates the frequencies and amplitudes of its components, with a view to limiting them (see Fi
43、gure 8) 3.15 frequency variations during transients or modulations of frequency, the instantaneous value of the frequency f of a non-periodic wave is deduced from the interval t between two consecutive passages of the wave to zero, by the formula: its speed (or rate) of variation is expressed in Hz/
44、s the frequency, or rate of repetition, of the frequency modulation is expressed in the number of occurrences (or periods) per second or minute 3.16 total harmonic content (current or voltage) the percentage of distortion (harmonics, modulation, etc.) compared with the sinusoidal basic wave it measu
45、res the ratio of the r.m.s. value of the total wave, reduced by the fundamental component, to the r.m.s. value of the fundamental periodic wave 3.17 individual harmonic content the ratio between the r.m.s. value of the fundamental component and the r.m.s. value of the fundamental periodic wave the h
46、armonic analysis4) or spectrum of distortion decomposes a periodic wave giving the amplitude of its components depending upon their frequency 4 Requirements common to all on-board systems 4.1 General conditions for power generation The requirements applicable to the systems shall permit them to prov
47、ide the types of operation in the conditions of use described and within the limits of the envelopes of Figure 6 and Figure 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 duri
48、ng the power supply to the aircraft by a ground support unit, in conformity with this standard. NOTEin case of specific 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
49、the parameters shall be the subject of an agreement between the interested parties, have the approval of the official Services and be specified in the particular specifications. 4.1.1 Supplied power In continuous steady-state conditions the power consumed on the system shall be between 5 % and 85 % of the available power. In transient conditions the power to be switched shall be compatible with the generator regulation. Examples: in normal frequent operation, establishment and cut-off from 5 % to
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