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1、 Reference number ISO 1540:2006(E) ISO 2006 INTERNATIONAL STANDARD ISO 1540 Third edition 2006-02-15 Aerospace Characteristics of aircraft electrical systems Aronautique Caractristiques des systmes lectriques bord des aronefs ISO 1540:2006(E) PDF disclaimer This PDF file may contain embedded typefac
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6、56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.org Web www.iso.org Published in Switzerland ii ISO 2006 All rights reserved ISO 1540:2006(E) ISO 2006 All rights reserved iii Contents Page Foreword iv Introduction v 1 Scope . 1 2 Normative references. 1 3 Terms
7、and definitions. 2 4 Requirements applicable to all systems 10 4.1 General. 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 ch
8、aracteristics 12 5.2 Steady-state characteristics 13 5.3 Transient characteristics . 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
9、. 16 7 D.C. power system characteristics. 19 7.1 General characteristics 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 switch
10、ing transients . 22 9.5 Inrush current 22 9.6 Input current modulation . 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
11、A.C. source equipment assumptions . 29 10.5 D.C. system assumptions 31 10.6 D.C. engine starting power quality 32 10.7 270 V d.c. input power 32 ISO 1540:2006(E) iv ISO 2006 All rights reserved Foreword ISO (the International Organization for Standardization) is a worldwide federation of national st
12、andards bodies (ISO member bodies). The work of preparing International Standards is normally carried 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 o
13、rganizations, governmental and non-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted in accordance with the rules giv
14、en in the ISO/IEC Directives, Part 2. The main task of technical committees is to prepare International 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
15、75 % of the member bodies casting a vote. Attention is drawn to the possibility that some of the elements 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, Air
16、craft and space vehicles, Subcommittee SC 1, Aerospace electrical requirements. This third edition cancels and replaces the second edition (ISO 1540:1984), which has been technically revised. ISO 1540:2006(E) ISO 2006 All rights reserved v Introduction The purpose of this International Standard is t
17、o foster compatibility between the providers, distributors and users of aircraft electrical power. This third edition takes into account several recent trends in aircraft electrical system, including that towards increased nonlinear load content on aircraft. It defines design requirements for electr
18、ical equipment that will be verified by the test requirements specified in ISO 7137. Limits defined in this International Standard are based upon historical as well as near term projected equipment characteristics, including recent trends towards increased nonlinear, electronic user equipment. Since
19、 these limits are influenced by the overall combination of source, distribution and user equipment, background to their integration sensitivities is also included herein. The intention is to provide system integrator guidance, without restricting flexibility of means by which the specified interface
20、 characteristics are achieved. This revision also addresses several power types not at present common on large transport aircraft, 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 equip
21、ment needs to be usable on a wide range of new aircraft. This results in some penalties typically only realized on large aircraft, e.g. those associated with longer distribution feeder voltage drops, being accepted for smaller aircraft equipment. The realities of these situations and recent user equ
22、ipment trends may likely be the reason for differences between this International Standard and other historical standards. INTERNATIONAL STANDARD ISO 1540:2006(E) ISO 2006 All rights reserved 1 Aerospace Characteristics of aircraft electrical systems 1 Scope This International Standard specifies the
23、 characteristics of electrical power supplied to the terminals of electrical utilization equipment installed in an aircraft. It is intended to support the interface definition for user equipment designed to accept electrical power on a variety of new civil aircraft applications, such as those certif
24、ied 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 follow this International Standard because of the penalties associated with multi-application. This document also attempts to
25、 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 this electrical power is a result of the combined characteristics of the electrical power source, distribution and user e
26、quipment. While only user equipment restrictions are specifically defined, background to key source and distribution equipment interfaces are identified in order to support development of the overall system. A wide variety of electrical supply types and distribution parameters have been considered,
27、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 support equipment. Distribution voltages addressed are nominal 14 V, 28 V and 42 V d.c.; nominal 26 V a.c., 400 Hz, one-p
28、hase; 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 which includes 400 Hz. 2 Normative references The following referenced documents are indispensable for the application of th
29、is document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 6858, Aircraft Ground support electrical supplies General requirements ISO 7137:1995, Aircraft Environmental conditions and
30、 test procedures for airborne equipment 1) 1) Endorsement of EUROCAE ED-14C and RTCA/DO-160C. ISO 1540:2006(E) 2 ISO 2006 All rights reserved 3 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1 abnormal electrical system operation aircraft operat
31、ion 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 limits for abnormal power quality are exceeded NOTE Once initiated, abnormal operation may co
32、ntinue 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 at user terminals during abnormal operation that take into account the operating tolerance
33、s 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. waveform measured under steady-state conditions NOTE 1 It is unitless and the ratio for a true
34、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 repeating current variation NOTE Measurable current modulation by user equipment can impact the q
35、uality 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 alternating (ripple) component on the d.c. level in a d.c. system NOTE a.c. system distortion
36、 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 occur at non-integer multiples of the fundamental frequency. These and all other elements of
37、 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 the fundamental frequency) and the input voltage (provided at the fundamental frequency) NOT
38、E 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 definition. (See also 3.35.) ISO 1540:2006(E) ISO 2006 All rights reserved 3 3.7 distortion factor (
39、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: 22 rms1 1 () (per cent)100 XX df X = where Xrms is the rms value of the complete (voltage or current) waveform;
40、 X1 is 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. or d.c. distortion NOTE 1 Its components may be harmo
41、nic 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 this International Standard to clearly separate requir
42、ements 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 1. 3.10 drift extremely slow variation in a random man
43、ner 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 parameter NOTE Drift rate is typically expressed in Hz/min
44、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 auxiliary power unit NOTE 1 Normal voltage transient limits
45、 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 rotating and static electrical power sources and the device
46、s which provide their control and protection ISO 1540:2006(E) 4 ISO 2006 All rights reserved 3.14 electric power system combination of electrical power sources, conversion equipment, control and protective devices and utilization equipment connected via a distribution network NOTE Also called simply
47、 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 a reduced complement of
48、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 essentia
49、l 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 the aircraft is not in flight NOTE It may be either a point-of-use or centrally located ground power electrical supply in land-based facilities, or a shipboard power supply in marine applications. 3.18 frequency reciprocal of the period of the a.c. waveform NOTE 1 Frequency is measure