ASD-STAN PREN 4660-004-2018 Aerospace series - Modular and open avionics architectures - Part 004 Packaging (Edition P 2).pdf

《ASD-STAN PREN 4660-004-2018 Aerospace series - Modular and open avionics architectures - Part 004 Packaging (Edition P 2).pdf》由会员分享，可在线阅读，更多相关《ASD-STAN PREN 4660-004-2018 Aerospace series - Modular and open avionics architectures - Part 004 Packaging (Edition P 2).pdf（35页珍藏版）》请在麦多课文档分享上搜索。

1、 ASD-STAN STANDARD NORME ASD-STAN ASD-STAN NORM ASD-STAN prEN 4660-004 Edition P2 2018-04 PUBLISHED BY THE AEROSPACE AND DEFENCE INDUSTRIES ASSOCIATION OF EUROPE - STANDARDIZATION Rue Montoyer 10 - 1000 Brussels - Tel. + 32 2 775 8126 - Fax. + 32 2 775 8131 - www.asd-stan.org ICS: Descriptors: ENGLI

2、SH VERSION Aerospace series Modular and open avionics architectures Part 004: Packaging Luft- und Raumfahrt Modulare und offene Avionikarchitekturen Teil 004: Paketierung Srie arospatiale Architectures avioniques modulaires et ouvertes Partie 004 : Packaging This “Aerospace Series“ Prestandard has b

3、een drawn up under the responsibility of ASD-STAN (The AeroSpace and Defence Industries Association of Europe - Standardization). It is published for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subse

4、quent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of ASD-STAN, the ASD-STAN prEN

5、will be submitted as a draft European Standard (prEN) to CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national members have then to implement the EN at national level by giving the EN the status of a national standard and by

6、withdrawing any national standards conflicting with the EN. ASD-STAN Technical Committee approves that: “This document is published by ASD-STAN for the needs of the European Aerospace Industry. The use of this standard is entirely voluntary, and its applicability and suitability for any particular u

7、se, including any patent infringement arising therefrom, is the sole responsibility of the user.” ASD-STAN reviews each standard and technical report at least every five years at which time it may be revised, reaffirmed, stabilized or cancelled. ASD-STAN invites you to send your written comments or

8、any suggestions that may arise. All rights reserved. No parts of this publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without prior written permission of ASD-STAN. Order details: E

9、-mail: salesasd-stan.org Web address: http:/www.asd-stan.org/ Edition approved for publication 1stApril 2018 Comments should be sent within six months after the date of publication to ASD-STAN General Domain prEN 4660-004:2018 (E) 2 Contents Page Introduction 3 1 Scope 4 2 Normative references 4 3 T

10、erms and definitions and abbreviations 6 4 Generic module specification 10 5 Module mechanical tests . 21 6 Guidelines for a rack slot . 23 7 Typical modular avionics environment . 24 (informative) Standard evolution form . 35 Annex AprEN 4660-004:2018 (E) 3 Introduction The purpose of this MOAA sta

11、ndard is to define a set of open architecture standards, concepts improved mission performance; improved operational performance. The MoAA standards are organised as a set of documents including: a set of agreed standards that describe, using a top down approach, the Architecture overview to all int

12、erfaces required to implement the core within avionics system; the guidelines for system implementation through application of the standards. The document hierarchy is given hereafter: (in this figure the document is highlighted). Figure 1 MOAA Standard Documentation Hierarchy prEN 4660-004:2018 (E)

13、 4 1 Scope This standard establishes uniform requirements for Packaging for the Common Functional Modules (CFM) within an Integrated Modular Avionic (IMA) system. It comprises the module physical properties and the Module Physical Interface (MPI) definitions together with guidelines for IMA rack and

14、 the operational environment. The characteristics addressed by the Packaging Standard are: Interchangeability: For a given cooling method all modules conforming to the packaging standard will function correctly when inserted into any rack slot conforming to the standard for the cooling method. All m

15、odules conforming to the Module Physical Interface (MPI) definitions for connector, IED and cooling interface will function correctly when inserted into any rack slot conforming to the same MPI definition. Maintainability: All modules are easily removable at first line. No special tools required at

16、first line. No manual adjustment is necessary when installing modules. No tool is required for installation or removal of the modules. Mechanical keying is provided that prevents insertion of a module into a rack slot that may cause an unsafe condition. The Module Physical Interface definition, cont

17、ained within this standard, does not include the properties of the signalling used in the optical interface (e. g. wavelength). These are covered in EN 4660-003. 2 Normative references The following documents are referred to in the text in such a way that some or all of their content constitutes req

18、uirements 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. EN 2101, Aerospace series Chromic acid anodizing of aluminium and wrought aluminium alloys EN 2284, Aerospace se

19、ries Sulphuric acid anodizing of aluminium and wrought aluminium alloys EN 2437, Aerospace series Chromate conversion coatings (yellow) for aluminium and aluminium alloys EN 4165 (all parts), Aerospace Series Connectors, electrical, rectangular, modular Operating temperature 175 C continuous EN 4660

20、-001, Aerospace series Modular and Open Avionics Architectures Part 001: Architecture EN 4660-002, Aerospace series Modular and Open Avionics Architectures Part 002: Common Functional Modules prEN 4660-004:2018 (E) 5 EN 4660-003, Aerospace series Modular and Open Avionics Architectures Part 003: Com

21、muni-cations/Network EN 4660-005, Aerospace series Modular and Open Avionics Architectures Part 005: Software ASAAC2-GUI-32450-001-CPG Issue 01, Final Draft of Guidelines for System Issues1) Volume 1 System Management. Volume 2 Fault Management. Volume 3 Initialisation and Shutdown. Volume 4 Configu

22、ration / Reconfiguration. Volume 5 Time Management. Volume 6 Security. Volume 7 Safety. ARINC 600, Air transport avionics Equipment interfaces2)ARINC 650, Integrated Modular Avionics Packaging and Interfaces2)ARINC 836, Cabin Standard Enclosures Modular Rack Principle (MRP)2)VITA 46, VPX: Baseline3)

23、Def Stan 03-18, Chromate Conversion Coatings (Chromate Filming Treatments) Grades: Standard and Brushing for Aluminium and Aluminium Alloys4)Def Stan 03-24, Chromic Acid Anodizing of Aluminium and Aluminium Alloys4)Def Stan 03-25, Sulphuric Acid Anodizing of Aluminium and Aluminium Alloy4)BS 5599, S

24、pecification for hard anodic oxidation coatings on aluminium and its alloys for engineering purposes 5)MIL-C-26074E, Coatings, Electroless Nickel Requirements6)MIL-A-8625E, Anodic Coatings for Aluminium and Aluminium Alloys6)MIL-C-81706, Chemical Conversion Materials for Coating Aluminium and Alumin

25、ium Alloys6)MIL-C-5541, Chemical Conversion Coatings on Aluminium and Aluminium Alloys6)1) In preparation at the date of publication of this standard. 2) Published by: ARINC, www.aviation- 3) Published by: VMEbus International Trade Association (VITA), 4) Published by: UK Ministry of Defence, www.d

26、stan.mod.uk 5) Published by: British Standards Institution (BSI), 6) Published by: DoD National (US) Mil. Department of Defense http:/www.defenselink.mil/ prEN 4660-004:2018 (E) 6 3 Terms and definitions and abbreviations For the purposes of this document, the following terms and definitions apply.

27、 3.1 General Use of “shall”, “should” and “may” within the standards observe the following rules: The word SHALL in the text express a mandatory requirement of the standard. The word SHOULD in the text expresses a recommendation or advice on implementing such a requirement of the standard. It is exp

28、ected that such recommendations or advice will be followed unless good reasons are stated for not doing so. The word MAY in the text expresses a permissible practice or action. It does not express a requirement of the standard. 3.2 Abbreviations AFA Air Flow Around AFT Air Flow Through ARINC Aeronau

29、tical Radio Inc ASAAC Allied Standard Avionics Architecture Council CC Conduction Cooled CFM Common Functional Module DAF Direct Air Flow EMC ElectroMagnetic Compatibility IED Insertion Extraction Device IMA Integrated Modular Avionics MBU Multiple Bit Upset MPI Module Physical Interface MT Mechanic

30、al Transfer NBC Nuclear, Biological and Chemical PSD Power Spectral Density SEU Single Event Upset prEN 4660-004:2018 (E) 7 3.3 Precedence Figures in this document have precedence over text. 3.4 Terms and definitions 3.4.1 General terms 3.4.1.1 backplane structure containing optical and electrical c

31、ommunication paths and electrical power supply wiring between modules. This shall be a removable structure or integrated into the rack. 3.4.1.2 cassette mechanical frame enclosing the electrical components of the module. 3.4.1.3 connector device to provide all of the electrical and optical connectio

32、ns between the cassette and the backplane. Note 1 to entry: The connector fixed to the module cassette plugs into the corresponding connector of the backplane. Note 2 to entry: It comprises a shell, inserts contacts and ferrules. 3.4.1.4 contact single signal connection, either an electrical pin/soc

33、ket or a single fibre. Note 1 to entry: In the case of fibre optic contacts this does not necessarily imply the mating parts are in mechanical contact. 3.4.1.5 cooling Interface surface which contributes to the removal of heat from the module. 3.4.1.6 ferrule housing and alignment device for one or

34、more optical fibres. 3.4.1.7 insert section of a connector containing a number of ferrules or contacts. 3.4.1.8 Insertion Extraction Device (IED) device to aid the insertion and extraction of the module from the rack and give mechanical advantage over the mating forces associated with the connector.

35、 It also provides the retention system for the module within the rack such that the module connector remains mated under all conditions specified. prEN 4660-004:2018 (E) 8 3.4.1.9 module grouping of electronic devices, assembled together to perform a specific function, into a flight-line protected h

36、ardware assembly. Note 1 to entry: This is the Common Functional Module. Note 2 to entry: The CFM is replaceable at first line. 3.4.1.10 rack mechanical arrangement for housing avionics equipment. This provides physical support, environmental protection and cooling for the modules. 3.4.1.11 shell ou

37、ter mating parts of the connector that provide the structure of the connector, fixings to the module and backplane parts and the support for the Inserts. 3.4.2 Module mechanical items A Common Functional Module comprises: a cassette; a connector; an insertion extraction device. The volume of the cas

38、sette is delimited by a cuboid. The module is referenced against a Cartesian Reference System as represented on Figure 2. prEN 4660-004:2018 (E) 9 Key 1 Side C 6 Side D 2 Side A 7 Insertion Direction 3 Module Header 8 Side B 4 Volume for Insertion/Extraction Device 9 Connector 5 Guide Edge 10 Refere

39、nce Plane Figure 2 Module definitions Guide Edge Edge of the CFM running along the X axis. It defines the location of the module within the rack. Height The cassette dimension in the Z-axis. It is measured from cassette Side C to cassette Side D. Length The cassette dimension in the X-axis measured

40、from the Reference Plane to the module header (this excludes the Insertion Extraction Device and the connector). Module header The surface of the cassette parallel to the Reference Plane, and opposite to the cassette surface contained within the Reference Plane The IED shall be mounted on this surfa

41、ce. prEN 4660-004:2018 (E) 10 Side A Surface of the cassette contained within the X, Z plane. Viewing the module in the direction of insertion, with the cassette Side C at the top, Side A is to the left. Side B Surface of the cassette parallel to and furthest from the X, Z plane. Viewing the module

42、in the direction of insertion, with the cassette Side C at the top, Side B is to the right. Side C Surface of the cassette parallel to and furthest from the X, Y plane. It contains one of the two cassette cooling interfaces, the other being within Side D. Side D Surface of the cassette contained wit

43、hin the X, Y plane. It contains one of the two cassette cooling interfaces, the other being within Side C. Reference Plane Plane defined by the Y and Z axis. It is perpendicular to the direction of insertion of the module and passes through the mating surface between the cassette and the connector.

44、Width The cassette dimension in the Y-axis of the module, measured from Side A to Side B. 3.4.3 Tolerances Unless otherwise stated, tolerances shall be 0,2 mm. 4 Generic module specification 4.1 Introduction This clause specifies the physical properties and the principle physical interfaces for MOAA

45、 Common Functional Modules, i.e. the Module Physical Interface (MPI). The MPI comprises: the Connector Interface between Common Functional Module and Backplane; the Cooling Interface; the Insertion Extraction Device (IED). The MoAA Common Functional Module supports four cooling techniques. These bei

46、ng: Conduction Cooling (CC); Direct Air Flow Cooling (DAF); Air Flow Around Cooling (AFA); Air Flow Through Cooling (AFT). It is assumed that a System Design Specification will be raised for each specific project implementation. It will define the CFM characteristics which are not imposed by the sta

47、ndard. prEN 4660-004:2018 (E) 11 4.2 Module description A module consists of an enclosed component mounting area, a connector and an insertion extraction device. The module shall have the following attributes: Provision for the protection of electronic devices, contained within the CFM, from the typ

48、ical environment requirements identified in the Clause 7, both during use and during handling, storage and transportation. Provision for a connector which mates with the backplane assembly and provides all power and data links to the rest of the avionics system. Provision for a keying method to posi

49、tively bulk the incorrect insertion of any CFM into a rack and to ensure that an incorrectly fitted CFM shall be prevented from making any electrical connection. Provision for a mechanism that retains the module within the rack under the mechanical and environmental conditions specified herein and yet allows for easy insertion and removal of the module. Provision for a cooling interface that provid