1、BRITISH STANDARDBS ISO 1540:2006Aerospace Characteristics of aircraft electrical systemsICS 49.060g49g50g3g38g50g51g60g44g49g42g3g58g44g55g43g50g56g55g3g37g54g44g3g51g40g53g48g44g54g54g44g50g49g3g40g59g38g40g51g55g3g36g54g3g51g40g53g48g44g55g55g40g39g3g37g60g3g38g50g51g60g53g44g42g43g55g3g47g36g58BS
2、 ISO 1540:2006This British Standard was published under the authority of the Standards Policy and Strategy Committee on 28 April 2006 BSI 2006ISBN 0 580 48211 1National forewordThis British Standard reproduces verbatim ISO 1540:2006 and implements it as the UK national standard.The UK participation
3、in its preparation was entrusted to Technical Committee ACE/6, Aerospace avionic electrical and fibre optic technology, which has the responsibility to:A list of organizations represented on this committee can be obtained on request to its secretary.Cross-referencesThe British Standards which implem
4、ent international publications referred to in this document may be found in the BSI Catalogue under the section entitled “International Standards Correspondence Index”, or by using the “Search” facility of the BSI Electronic Catalogue or of British Standards Online.This publication does not purport
5、to include all the necessary provisions of a contract. Users are responsible for its correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. aid enquirers to understand the text; present to the responsible international/European committee an
6、y enquiries on the interpretation, or proposals for change, and keep UK interests informed; monitor related international and European developments and promulgate them in the UK.Summary of pagesThis document comprises a front cover, an inside front cover, the ISO title page, pages ii to v, a blank p
7、age, pages 1 to 56, an inside back cover and a back cover.The BSI copyright notice displayed in this document indicates when the document was last issued.Amendments issued since publicationAmd. No. Date CommentsReference numberISO 1540:2006(E)INTERNATIONAL STANDARD ISO1540Third edition2006-02-15Aero
8、space Characteristics of aircraft electrical systems Aronautique Caractristiques des systmes lectriques bord des aronefs BS ISO 1540:2006ii iiiContents Page Foreword iv Introduction v 1 Scope . 1 2 Normative references . 1 3 Terms and definitions. 2 4 Requirements applicable to all systems 10 4.1 Ge
9、neral. 10 4.2 On-aircraft power sources . 10 4.3 External power sources . 11 4.4 Source/distribution system coordination.11 4.5 Utilization equipment 11 5 Constant frequency (CF) a.c. power system characteristics . 12 5.1 General characteristics 12 5.2 Steady-state characteristics 13 5.3 Transient c
10、haracteristics . 13 6 Variable frequency (VF) a.c. power system characteristics. 15 6.1 General characteristics 15 6.2 Consideration of CF power characteristics . 15 6.3 Steady-state characteristics 15 6.4 Transient characteristics . 16 7 D.C. power system characteristics . 19 7.1 General characteri
11、stics 19 7.2 Steady-state characteristics 19 7.3 Transient characteristics . 20 8 Requirements allocation 21 9 Utilization equipment restrictions. 21 9.1 General. 21 9.2 A.C. power utilization . 21 9.3 Power factor 21 9.4 Load switching transients . 22 9.5 Inrush current 22 9.6 Input current modulat
12、ion . 22 9.7 Input current distortion 22 9.8 Maximum input capacitance 23 10 Power quality associated assumptions and background 24 10.1 General. 24 10.2 Background to the document scope 25 10.3 A.C. power system assumptions 25 10.4 A.C. source equipment assumptions .29 10.5 D.C. system assumptions
13、31 10.6 D.C. engine starting power quality 32 10.7 270 V d.c. input power 32 BS ISO 1540:2006iv Foreword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is normally carr
14、ied out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work.
15、ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 2. The main task of technical committees is to prepare Internat
16、ional Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting a vote. Attention is drawn to the possibility that some of the e
17、lements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 1540 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 1, Aerospace electrical requirements. This third edition
18、 cancels and replaces the second edition (ISO 1540:1984), which has been technically revised. BS ISO 1540:2006vIntroduction The purpose of this International Standard is to foster compatibility between the providers, distributors and users of aircraft electrical power. This third edition takes into
19、account several recent trends in aircraft electrical system, including that towards increased nonlinear load content on aircraft. It defines design requirements for electrical equipment that will be verified by the test requirements specified in ISO 7137. Limits defined in this International Standar
20、d are based upon historical as well as near term projected equipment characteristics, including recent trends towards increased nonlinear, electronic user equipment. Since these limits are influenced by the overall combination of source, distribution and user equipment, background to their integrati
21、on sensitivities is also included herein. The intention is to provide system integrator guidance, without restricting flexibility of means by which the specified interface characteristics are achieved. This revision also addresses several power types not at present common on large transport aircraft
22、, such as variable frequency a.c., 230/400 V a.c. and 42 V d.c. Also fundamental to the basis of these requirements is the assumption that cost-effective utilization equipment needs to be usable on a wide range of new aircraft. This results in some penalties typically only realized on large aircraft
23、, e.g. those associated with longer distribution feeder voltage drops, being accepted for smaller aircraft equipment. The realities of these situations and recent user equipment trends may likely be the reason for differences between this International Standard and other historical standards. BS ISO
24、 1540:2006blank1Aerospace Characteristics of aircraft electrical systems 1 Scope This International Standard specifies the characteristics of electrical power supplied to the terminals of electrical utilization equipment installed in an aircraft. It is intended to support the interface definition fo
25、r user equipment designed to accept electrical power on a variety of new civil aircraft applications, such as those certified via the Technical Standard Order (TSO) certification process. It might not be desirable for equipment targeted to a single application or specific military application to fol
26、low this International Standard because of the penalties associated with multi-application. This document also attempts to provide background to the development of these requirements that may be useful to those designing and/or integrating modern aircraft electrical systems. The delivered quality of
27、 this electrical power is a result of the combined characteristics of the electrical power source, distribution and user equipment. While only user equipment restrictions are specifically defined, background to key source and distribution equipment interfaces are identified in order to support devel
28、opment of the overall system. A wide variety of electrical supply types and distribution parameters have been considered, as may be found on both small and large transport aircraft. Sources considered include physically rotating and static types, provided either on-aircraft, or as part of the ground
29、 support equipment. Distribution voltages addressed are nominal 14 V, 28 V and 42 V d.c.; nominal 26 V a.c., 400 Hz, one-phase; nominal 115/200 V rms and 230/400 V rms a.c., both one-phase and three-phase, at either a nominal 400 Hz constant frequency (CF), or over a variable frequency (VF) range wh
30、ich includes 400 Hz. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 6
31、858, Aircraft Ground support electrical supplies General requirements ISO 7137:1995, Aircraft Environmental conditions and test procedures for airborne equipment 1)1) Endorsement of EUROCAE ED-14C and RTCA/DO-160C. BS ISO 1540:20062 3 Terms and definitions For the purposes of this document, the foll
32、owing terms and definitions apply. 3.1 abnormal electrical system operation aircraft operation where a malfunction or failure in the electrical system has taken place and the protective devices of the system are operating to remove the malfunction or failure from the rest of the system before the li
33、mits for abnormal power quality are exceeded NOTE Once initiated, abnormal operation may continue for the remainder of a flight with the power quality delivered to users exceeding normal operation limits, but staying within abnormal operation limits. 3.2 abnormal power quality limits limits provided
34、 at user terminals during abnormal operation that take into account the operating tolerances of the system protective devices and any inherently limiting characteristics of the system design NOTE See also 3.30. 3.3 crest factor absolute value of the ratio of the peak to the rms value of an a.c. wave
35、form measured under steady-state conditions NOTE 1 It is unitless and the ratio for a true sine wave is equal to 2 . NOTE 2 Written as | (pk) / (rms) |VV . 3.4 current modulation difference between the maximum and minimum value of electrical current drawn during conditions of cyclic or randomly repe
36、ating current variation NOTE Measurable current modulation by user equipment can impact the quality and/or stability of the provided electrical power. 3.5 distortion (current or voltage) rms value of the a.c. waveform exclusive of the fundamental component in an a.c. system, or the rms value of the
37、alternating (ripple) component on the d.c. level in a d.c. system NOTE a.c. system distortion can include harmonic and non-harmonic components. Harmonics are sinusoidal distortion components which occur at integer multiples of the fundamental frequency. Interharmonics are distortion components which
38、 occur at non-integer multiples of the fundamental frequency. These and all other elements of waveform distortion are included in this general definition of distortion. (See also 3.23 and 3.25.) 3.6 displacement factor a.c. user equipment cosine of the angle () between the input current (provided at
39、 the fundamental frequency) and the input voltage (provided at the fundamental frequency) NOTE This value does not include the effect of distortion in the input current (and/or voltage) waveform, and it is therefore not applied in this specification in favour of the more general power factor definit
40、ion. (See also 3.35.) BS ISO 1540:200633.7 distortion factor (current or voltage) ratio of the distortion in a waveform to the rms value of the fundamental component of the waveform NOTE 1 The distortion factor is typically expressed as a percentage: 22rms 11()(per cent) 100XXdfX= where Xrmsis the r
41、ms value of the complete (voltage or current) waveform; X1is the rms value of the fundamental frequency component. NOTE 2 In a d.c. system, this fundamental component is true d.c. (See also 3.5, 3.43.) 3.8 distortion spectrum itemization of the amplitude of each frequency component found in the a.c.
42、 or d.c. distortion NOTE 1 Its components may be harmonic or non-harmonic multiples of the fundamental frequency, some of which result from amplitude or frequency modulation. NOTE 2 Only components up to a frequency of 16 kHz (for 400 Hz, CF equipment) and 32 kHz (for VF equipment) are addressed in
43、this International Standard to clearly separate requirements related to electrical power quality from those related to electromagnetic compatibility (EMC). 3.9 distribution system collection of interconnection and circuit protection equipment between power sources and user equipment NOTE See Figure
44、1. 3.10 drift extremely slow variation in a random manner of a controlled parameter (such as frequency in a CF system) inside of the specification limits from causes such as ageing of components or self-induced temperature changes 3.11 drift rate speed of variation due to drift of a controlled param
45、eter NOTE Drift rate is typically expressed in Hz/min or V/min, depending upon the parameter examined. 3.12 electric engine start operation special case of normal electrical system operation where an extreme demand of electrical power is required to support the starting of a main engine or the auxil
46、iary power unit NOTE 1 Normal voltage transient limits may be exceeded during this condition with only selected utilization equipment required to operate throughout the event. NOTE 2 Typical engine start times are between 15 s and 90 s. 3.13 electric power generating system EPGS combination of rotat
47、ing and static electrical power sources and the devices which provide their control and protection BS ISO 1540:20064 3.14 electric power system combination of electrical power sources, conversion equipment, control and protective devices and utilization equipment connected via a distribution network
48、 NOTE Also called simply system. 3.15 emergency electric system operation electrical system condition during flight when the primary electric power system becomes unable to supply sufficient or proper electrical power, thus requiring the use of independent and potentially limited source(s) to power
49、a reduced complement of distribution and utilization equipment selected to maintain safe flight and personnel safety 3.16 emergency power source generator, power conversion device (or a combination thereof not involving part of utilization equipment) or battery installed to provide independent electrical power for essential purposes during conditions of electrical emergency in flight 3.17 external power unit ground power unit GPU rotating or static source (or combination thereof) supplied by the maintenance facility to source electrical power demands while
