1、BRITISH STANDARDBS EN 4533-001:2006Aerospace series Fibre optic systems Handbook Part 001: Termination methods and toolsThe European Standard EN 4533-001:2006 has the status of a British StandardICS 49.060g49g50g3g38g50g51g60g44g49g42g3g58g44g55g43g50g56g55g3g37g54g44g3g51g40g53g48g44g54g54g44g50g49
2、g3g40g59g38g40g51g55g3g36g54g3g51g40g53g48g44g55g55g40g39g3g37g60g3g38g50g51g60g53g44g42g43g55g3g47g36g58BS EN 4533-001:2006This British Standard was published under the authority of the Standards Policy and Strategy Committee on 31 October 2006 BSI 2006ISBN 0 580 49446 2National forewordThis Britis
3、h Standard was published by BSI. It is the UK implementation of EN 4533-001:2006. The UK participation in its preparation was entrusted by Technical Committee ACE/6, Aerospace avionic electrical and fibre optic technology, to Subcommittee ACE/6/-/10, Aerospace Fibre optic systems and equipment.A lis
4、t of organizations represented on ACE/6/-/10 can be obtained on request to its secretary.This publication does not purport to include all the necessary provisions of a contract. Users are responsible for its correct application.Compliance with a British Standard cannot confer immunity from legal obl
5、igations.Amendments issued since publicationAmd. No. Date CommentsEUROPEAN STANDARDNORME EUROPENNEEUROPISCHE NORMEN 4533-001July 2006ICS 49.060English VersionAerospace series - Fibre optic systems - Handbook - Part 001:Termination methods and toolsSrie arospatiale - Systmes des fibres optiques - Man
6、ueldutilisation - Partie 001 : Mthodes des terminaisons etoutilsLuft- und Raumfahrt - Faseroptische Systemtechnik -Handbuch - Teil 001: Verarbeitungsmethoden undWerkzeugeThis European Standard was approved by CEN on 28 April 2006.CEN members are bound to comply with the CEN/CENELEC Internal Regulati
7、ons which stipulate the conditions for giving this EuropeanStandard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such nationalstandards may be obtained on application to the Central Secretariat or to any CEN member.This European
8、 Standard exists in three official versions (English, French, German). A version in any other language made by translationunder the responsibility of a CEN member into its own language and notified to the Central Secretariat has the same status as the officialversions.CEN members are the national st
9、andards bodies of Austria, Belgium, Cyprus, Czech Republic, Denmark, Estonia, Finland, France,Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania,Slovakia, Slovenia, Spain, Sweden, Switzerland and United Kingdom.EURO
10、PEAN COMMITTEE FOR STANDARDIZATIONCOMIT EUROPEN DE NORMALISATIONEUROPISCHES KOMITEE FR NORMUNGManagement Centre: rue de Stassart, 36 B-1050 Brussels 2006 CEN All rights of exploitation in any form and by any means reservedworldwide for CEN national Members.Ref. No. EN 4533-001:2006: E2 Contents Page
11、 Foreword4 Introduction .5 1 Scope 6 1.1 General6 1.2 Need for high integrity terminations6 2 Normative references 6 3 Component selection 7 3.1 Elements.7 3.2 Fibre optic cables 7 3.2.1 General7 3.2.2 Cable construction 7 3.2.3 Fibre choice8 3.2.4 Cladding materials.8 3.3 Primary coating materials.
12、8 3.3.1 Function8 3.3.2 Acrylate.8 3.3.3 Polyimide 9 3.3.4 Silicone .9 3.4 Aramid yarn versus fibreglass strength member.9 3.5 Fibre optic connectors 9 3.5.1 Purpose.9 3.5.2 Connector types.9 4 Health and safety aspects 13 4.1 General. 13 4.2 Chemicals 13 4.3 “Sharps” 13 5 Termination process 14 5.1
13、 Objective 14 5.2 Cable preparation . 14 5.2.1 General. 14 5.2.2 Cutting to length . 14 5.2.3 Removal of outer jacket . 15 5.2.4 Strength member trimming/removal. 18 5.3 Removal of secondary coating(s) . 19 5.4 Removal of primary coating 19 5.4.1 General. 19 5.4.2 Mechanical techniques for primary c
14、oating removal 20 5.4.3 Alternative techniques . 24 5.4.4 Removal of troublesome coatings 26 5.4.5 Evidence of strength reduction when stripping primary buffer coatings. 26 5.4.6 To clean or not to clean . 27 5.5 Adhesives 28 5.5.1 General. 28 5.5.2 Adhesive types 28 5.5.3 The importance of glass tr
15、ansition temperature (Tg) . 30 5.5.4 Epoxy cure schedules 30 5.5.5 Usability. 32 5.5.6 Qualification 33 5.6 Connector preparation . 33 EN 4533-001:20063 5.6.1 Dry fitting (Dont do it) 33 5.6.2 Cleanliness.34 5.7 Sleeves, boots and backshells 34 5.8 Attachment of fibre to connector.35 5.8.1 Applicati
16、on of adhesive 35 5.8.2 Inserting fibre best-practice .36 5.9 Adhesive cure37 5.9.1 General .37 5.9.2 Orientation .37 5.9.3 Curing equipment37 5.10 Excess fibre removal.39 5.10.1 General .39 5.10.2 Post-cure rough cleaving .40 5.10.3 Pre-cleave.41 5.10.4 Cleaving tools 41 5.11 Polishing 42 5.11.1 Ra
17、tionale 42 5.11.2 Performance metrics.42 5.11.3 End-face geometry parameters43 5.11.4 Methods for achieving end-face geometry .44 5.11.5 Polishing stages45 5.11.6 Polishing tools and equipment 49 5.12 Inspection.54 Bibliography55 EN 4533-001:20064 Foreword This European Standard (EN 4533-001:2006) h
18、as been prepared by the European Association of Aerospace Manufacturers - Standardization (AECMA-STAN). After enquiries and votes carried out in accordance with the rules of this Association, this Standard has received the approval of the National Associations and the Official Services of the member
19、 countries of AECMA, prior to its presentation to CEN. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest by January 2007, and conflicting national standards shall be withdrawn at the latest by January
20、2007. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN and/or CENELEC shall not be held responsible for identifying any or all such patent rights. According to the CEN/CENELEC Internal Regulations, the national standards organi
21、zations of the following countries are bound to implement this European Standard: Austria, Belgium, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slov
22、akia, Slovenia, Spain, Sweden, Switzerland and the United Kingdom. EN 4533-001:20065 Introduction a) The handbook This handbook draws on the work of the Fibre Optic Harness Study, part sponsored by the United Kingdoms Department of Trade and Industry, plus other relevant sources. It aims to provide
23、general guidance for experts and non-experts alike in the area of designing, installing, and supporting multi-mode fibre-optic systems on aircraft. Where appropriate more detailed sources of information are referenced throughout the text. It is arranged in 4 parts, which reflect key aspects of an op
24、tical harness life cycle, namely: Part 001: Termination methods and tools Part 002: Test and measurement Part 003: Looming and installation practices Part 004: Repair, maintenance and inspection b) Background It is widely accepted in the aerospace industry that photonic technology offers a number of
25、 significant advantages over conventional electrical hardware. These include massive signal bandwidth capacity, electrical safety, and immunity of passive fibre-optic components to the problems associated with electromagnetic interference (EMI). To date, the latter has been the critical driver for a
26、irborne fibre-optic communications systems because of the growing use of non-metallic aerostructures. However, future avionic requirements are driving bandwidth specifications from 10s of Mbits/s into the multi-Gbits/s regime in some cases, i.e. beyond the limits of electrical interconnect technolog
27、y. The properties of photonic technology can potentially be exploited to advantage in many avionic applications, such as video/sensor multiplexing, flight control signalling, electronic warfare, and entertainment systems, as well as in sensing many of the physical phenomena on-board aircraft. The ba
28、sic optical interconnect fabric or optical harness is the key enabler for the successful introduction of optical technology onto commercial and military aircraft. Compared to the mature telecommunications applications, an aircraft fibre-optic system needs to operate in a hostile environment (e.g. te
29、mperature extremes, humidity, vibrations, and contamination) and accommodate additional physical restrictions imposed by the airframe (e.g. harness attachments, tight bend radii requirements, and bulkhead connections). Until recently, optical harnessing technology and associated practices were insuf
30、ficiently developed to be applied without large safety margins. In addition, the international standards did not adequately cover many aspects of the life cycle. The lack of accepted standards thus lead to airframe specific hardware and support. These factors collectively carried a significant cost
31、penalty (procurement and through-life costs), that often made an optical harness less competitive than an electrical equivalent. c) The fibre-optic harness study The Fibre-Optic Harness Study concentrated on developing techniques, guidelines, and standards associated with the through-life support of
32、 current generation fibre-optic harnesses applied in civil and military airframes (fixed and rotary wing). Some aspects of optical system design were also investigated. This programme has been largely successful. Guidelines and standards based primarily on harness study work are beginning to emerge
33、through a number of standards bodies. Because of the aspects covered in the handbook, European prime contractors are in a much better position to utilise and support available fibre optic technology. EN 4533-001:20066 1 Scope 1.1 General This Part of EN 4533 examines the termination aspects of fibre
34、 optic design for avionic installations. By termination is meant the mechanism used to interface from one component (usually a fibre) to another. This is normally performed by a connector, which aligns the fibre with another component (usually another connector) to a sufficient accuracy to allow con
35、tinued transmission of an optical signal throughout the operational envelope. This Part will explain the need for high integrity terminations, provide an insight into component selection issues and suggests best practice when terminating fibres into connectors for high integrity applications. A deta
36、iled review of the termination process can be found in Clause 4 of this part and is organised broadly in line with the sequence of a typical termination procedure. The vast number of cable constructions and connectors available make defining a single termination instruction that is applicable to all
37、 combinations almost impossible. Because of the problems of defining a generic termination instruction, this handbook has concentrated on defining best practice for current to near future applications of fibre optics on aircraft. This has limited the studies within this part to currently available a
38、vionic silica fibre cables and adhesive filled butt-coupled type connectors. Many of the principles described however would still be applicable for other termination techniques. Other types of termination are considered further in the repair part of this handbook. 1.2 Need for high integrity termina
39、tions In order to implement a fibre optic based system on an aircraft it is vital to ensure that the constituent elements of the system will continue to operate, to specification, over the life of the system. An important aspect of this requirement is the need for reliable interconnection components
40、. This is often expressed as the need for reliable connectors, but in reality it is the need for a reliable cable to connector termination process. The essence of this requirement is the need to assure reliable light transmission through each optical connector throughout the operational envelope. Th
41、is needs to be achieved through a robust process that enables a high level of optical performance over the lifetime of the terminations. Many factors can contribute to an optical connectors in-service performance, such as basic connector design, choice of optical fibre, cable, operating and maintena
42、nce environment etc. However, one of the main factors governing in-service connector performance is the quality of the cable to connector termination. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edit
43、ion cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. EN 4533-002, Aerospace series Fibre optic systems Handbook Part 002: Test and measurement. EN 4533-001:20067 3 Component selection 3.1 Elements It is important to recognize th
44、at a fibre optic termination, while appearing straightforward, is in fact a complex interaction of the constituent elements such as: fibre coatings, connector design, cable strength member anchorage method, adhesive type and cure regime (where used), material properties and so on. Each of these elem
45、ents will have an impact on the termination, in terms of reliability, integrity and process complexity. 3.2 Fibre optic cables 3.2.1 General One of the main aspects to be addressed is the implication of choosing one cable construction over another. There are various types of fibre optic cable on the
46、 market ranging from loose tube to tight jacket construction, containing a single fibre or an array of many fibres; however, at the time of publication of this handbook the range of options available to aerospace users is somewhat limited. Most of the possible cable types are only suitable for telec
47、ommunication applications due to environmental capability limitations, with avionic solutions being generally limited to single fibre, tight jacket constructions. 3.2.2 Cable construction Although the design of fibre optic cable for use on aircraft is fairly similar from one manufacturer to another
48、there are important differences between cables. The two main areas of difference are fibre coatings and cable strength member materials. Each has its own positive and negative attributes in the context of termination procedures. Avionic fibre optic cables are typically constructed as follows, see Fi
49、gures 1 and 2. Key 1 Outer jacket 2 Buffer 3 Cladding 4 Core 5 Primary coating 6 Strength member Figure 1 Typical avionic fibre optic cable construction 1 2 6 5 4 3 EN 4533-001:20068 Figure 2 Examples of typical avionic fibre optic cables 3.2.3 Fibre choice From the perspective of termination there is little difference between small and larger core optical fibres. The main fibre issues that impact upon the termination process relate to cladding and primary coating materials. Current generation of avionic fibre sizes tend to be larger than the
