1、ASD STANDARD NORME ASD ASD NORM prEN 4660-004 Edition P 1 July 2009 PUBLISHED BY THE AEROSPACE AND DEFENCE INDUSTRIES ASSOCIATION OF EUROPE - STANDARDIZATIONAvenue de Tervuren, 270 - B-1150 Brussels - Tel. + 32 2 775 8126 - Fax. + 32 2 775 8131 - www.asd-stan.orgICS: Descriptors: ENGLISH VERSION Aer
2、ospace series Modular and Open Avionics Architectures Part 004: Final draft of Proposed Standards for Packaging Srie arospatiale Architectures Avioniques Modulaires et Ouvertes Partie 004 : Dernire proposition des Standards pour Packaging Luft- und Raumfahrt Modulare und offene Avionikarchitekturen
3、Teil 004: Endgltiger Entwurf des Standards fr Packaging This “Aerospace Series“ Prestandard has been 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
4、been technically approved by the experts of the concerned Domain following member comments. Subsequent 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 sta
5、ndard. After examination and review by users and formal agreement of ASD-STAN, it 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 t
6、he EN at national level by giving the EN the status of a national standard and by withdrawing any national standards conflicting with the EN. Edition approved for publication 31 July 2009 Comments should be sent within six months after the date of publication to ASD-STAN Engineering Procedures Domai
7、n Copyright 2009 by ASD-STAN prEN 4660-004:2009 (E) 2 Contents Page Foreword4 0 Introduction5 0.1 Purpose.5 0.2 Document structure.6 1 Scope 6 2 Normative references 7 3 Terms, definitions and abbreviations8 3.1 Terms and definitions .8 3.2 Abbreviations.8 3.3 Precedence.9 3.4 Definition of terms .9
8、 4 Generic module specification 11 4.1 Introduction. 11 4.2 Module description. 12 4.3 Module Physical Specification 12 4.4 Module Physical Interface - Connector 16 4.5 Module Physical Interface - Cooling. 20 4.6 Module Physical Interface Insertion Extraction Device. 23 5 Module Mechanical Tests 25
9、5.1 Master gauge test . 25 5.2 Module insertion and extraction . 25 6 Guidelines for a rack slot. 27 6.1 Introduction. 27 6.2 Interchangeability . 27 6.3 Rack Slot Design Requirements . 27 6.4 Connector interface 28 6.5 Conduction Cooled Interface. 29 6.6 Air Flow Cooled Interface 30 6.7 Relationshi
10、p between Cooling, Connector and IED Rack Interfaces 32 7 Typical modular avionics environment 33 7.1 Ambient pressure (altitude). 34 7.2 Humidity. 34 7.3 High and low temperatures 34 7.4 Thermal shocks. 35 7.5 Salt spray. 36 7.6 Vibrations 36 7.7 Accelerations 37 7.8 Mechanical shocks . 38 7.9 Cont
11、amination resistance 39 7.10 Flame resistance. 39 7.11 Fungus resistance 39 7.12 Rain 39 7.13 Acoustic noise 40 7.14 Electromagnetic environment . 40 7.15 Explosive atmosphere 40 7.16 Nuclear, Biological and Chemical (NBC) Hazards. 40 7.17 Sand and dust . 42 7.18 Single Event Upset / Multiple Bit Up
12、set 42 7.19 Module Tempest 42 prEN 4660-004:2009 (E) 3 Figures Page Figure 1 ASAAC Standard Documentation Hierarchy .5 Figure 2 Module definitions 10 Figure 3 CFM dimensions .13 Figure 4 Module Connector Interface Definition and Identification (connector inserts shown for example only) .16 Figure 5
13、Preferred Contact Identification (viewed from outside module, lowest numbered contact is towards Side C of the cassette) .17 Figure 6 Contact Identification MT Ferrule.18 Figure 7 Polarisation Key identification 19 Figure 8 Conduction Cooled Module Cooling Interface Definition20 Figure 9 Air cooled
14、module Cooling interface definition22 Figure 10 IED Hook characteristics .24 Figure 11 IED Implementation example.25 Figure 12 Rack Connector Physical Interface.28 Figure 13 Conduction Cooled rack guide rail .29 Figure 14 Air Flow Through and Direct Air Flow cooled rack guide rail30 Figure 15 Air Fl
15、ow Around cooled rack guide rail31 Tables Page Table 1 Allowed aluminium protective treatments.14 Table 2 Ambient pressure in relation to altitude 34 Table 3 Temperature environmental conditions - Conditioned bay .35 Table 4 Temperature environmental conditions - Unconditioned bay.35 Table 5 Tempera
16、ture environmental conditions - Storage35 Table 6 Thermal shocks 36 Table 7 Sinusoidal vibrations .36 Table 8 Rotational accelerations37 Table 9 Transversal accelerations .38 Table 10 Functional Shocks .38 prEN 4660-004:2009 (E) 4 Table 11 Summary of environment and bonding environmental Conditions.
17、 40 Table 12 Initial Nuclear radiation conditions 41 Table 13 Nuclear hardening conditions 41 Foreword This standard was reviewed by the Domain Technical Coordinator of ASD-STANs Engineering Procedures Domain. After inquiries and votes carried out in accordance with the rules of ASD-STAN defined in
18、ASD-STANs General Process Manual, this standard has received approval for Publication. prEN 4660-004:2009 (E) 5 0 Introduction 0.1 Purpose This document is produced under contract ASAAC Phase II Contract n97/86.028. The purpose of the ASAAC Programme is to define and validate a set of open architect
19、ure standards, concepts and guidelines for Advanced Avionics Architectures (A3) in order to meet the three main ASAAC drivers. The standards, concepts and guidelines produced by the Programme are to be applicable to both new aircraft and update programmes from 2005. The three main goals for the ASAA
20、C Programme are: 1. Reduced life cycle costs. 2. Improved mission performance. 3. Improved operational performance. The ASAAC 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 interfaces requi
21、red 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) Guidelines for System Issues System Management Fault Management Initialisation / Sh
22、utdown Configuration / Reconfiguration Time Management Security Safety Standard for Architecture Standard for Common Functional ModulesStandard for Communications and Network Standard for Packaging Standard for Software Figure 1 ASAAC Standard Documentation Hierarchy prEN 4660-004:2009 (E) 6 0.2 Doc
23、ument structure The document contains the following sections: Section 1, Scope. Section 2, Normative references. Section 3, Terms, definitions and abbreviation. Section 4, Generic module specification. Section 5, Module Mechanical Tests. Section 6, Guidelines for a rack slot. Section 7, Typical modu
24、lar avionics environment. 1 Scope The purpose of this standard is to establish uniform requirements for Packaging for the Common Functional Modules (CFM) within an Integrated Modular Avionic (IMA) system, as defined per ASAAC. It comprises the module physical properties and the Module Physical Inter
25、face (MPI) definitions together with guidelines for IMA rack and 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 ra
26、ck slot conforming to the standard for the cooling method. All modules 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 a
27、re easily removable at first line. No special tools required at 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
28、unsafe condition. The Module Physical Interface definition, contained 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. prEN 4660-004:2009 (E) 7 2 Normative references This European Standard inco
29、rporates by dated or undated reference, provisions from other publications. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this Eur
30、opean Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies (including amendments). EN 2101, Aerospace series Chromic acid anodizing of aluminium and wrought aluminium alloys. EN 2284, Aerospace series Sulphur
31、ic acid anodizing of aluminium and wrought aluminium alloys. EN 2437, Aerospace series Chromate conversion coatings (yellow) for aluminium and aluminium alloys. EN 4660-001, Aerospace series Modular and open Avionics Architectures Part 001: Final Draft of Proposed Standards for Architecture. 1)EN 46
32、60-002, Aerospace series Modular and open Avionics Architectures Part 002: Final Draft of Proposed Standards for Common Functional Modules. 1)EN 4660-003, Aerospace series Modular and open Avionics Architectures Part 003: Final Draft of Proposed Standards for Communications/Network. 1)EN 4660-005, A
33、erospace series Modular and open Avionics Architectures Part 005: Final Draft of Proposed Standards for Software. 1)ASAAC2-GUI-32450-001-CPG Issue 01, Final Draft of Guidelines for System Issues 2) Volume 1 System Management. Volume 2 Fault Management. Volume 3 Initialisation and Shutdown. Volume 4
34、Configuration / Reconfiguration. Volume 5 Time Management. Volume 6 Security. Volume 7 Safety. ARINC 600, Air transport avionics Equipment interfaces. Def Stan 03-18, Chromate Conversion Coatings (Chromate Filming Treatments) Grades: Standard and Brushing for Aluminium and Aluminium Alloys. Def Stan
35、 03-24, Chromic Acid Anodizing of Aluminium and Aluminium Alloys. Def Stan 03-25, Sulphuric Acid Anodizing of Aluminium and Aluminium Alloys. 1) Published as ASD Prestandard at the date of publication of this standard. 2) In preparation at the date of publication of this standard. prEN 4660-004:2009
36、 (E) 8 BS 5599, Specification for hard anodic oxidation coatings on aluminium and its alloys for engineering purposes. 3)MIL-C-26074E, Coatings, Electroless Nickel Requirements. MIL-A-8625E, Anodic Coatings for Aluminium and Aluminium Alloys. MIL-C-81706, Chemical Conversion Materials for Coating Al
37、uminium and Aluminium Alloys. MIL-C-5541, Chemical Conversion Coatings on Aluminium and Aluminium Alloys. 3 Terms, definitions and abbreviations 3.1 Terms and definitions Use of “shall”, “should” and “may” within the standards observe the following rules: The word SHALL in the text express a mandato
38、ry 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 expected that such recommendations or advice will be followed unless good reasons are stated for not doing so. The word MAY in the text expresses
39、 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 Aeronautical Radio Inc ASAAC Allied Standard Avionics Architecture Council CC Conduction Cooled CFM Common Functional Module DAF Direct Air Flow EMC
40、ElectroMagnetic Compatibility IED Insertion Extraction Device IMA Integrated Modular Avionics MBU Multiple Bit Upset 3) Replaces Def Stan 03-26. prEN 4660-004:2009 (E) 9 MPI Module Physical Interface MT Mechanical Transfer NBC Nuclear, Biological and Chemical PSD Power Spectral Density SEU Single Ev
41、ent Upset 3.3 Precedence Figures in this document have precedence over text. 3.4 Definition of terms 3.4.1 General terms Backplane A structure containing optical and electrical communication paths and electrical power supply wiring between modules. This shall be a removable structure or integrated i
42、nto the rack. Cassette Mechanical frame enclosing the electrical components of the module. Connector A device to provide all of the electrical and optical connections between the cassette and the backplane. The connector fixed to the module cassette plugs into the corresponding connector of the back
43、plane. It comprises a shell, inserts contacts and ferrules. Contact A single signal connection, either an electrical pin/socket or a single fibre. In the case of fibre optic contacts this does not necessarily imply the mating parts are in mechanical contact. Cooling Interface Surface which contribut
44、es to the removal of heat from the module. Ferrule A housing and alignment device for one or more optical fibres. Insert A section of a connector containing a number of ferrules or contacts. Insertion Extraction Device (IED) A device to aid the insertion and extraction of the module from the rack an
45、d give mechanical advantage over the mating forces associated with the connector. It also provides the retention system for the module within the rack such that the module connector remains mated under all conditions specified. Module The module is a grouping of electronic devices, assembled togethe
46、r to perform a specific function, into a flight-line protected hardware assembly. This is the Common Functional Module. The CFM is replaceable at first line. Rack A mechanical arrangement for housing avionics equipment. This provides physical support, environmental protection and cooling for the mod
47、ules. Shell The outer 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. prEN 4660-004:2009 (E) 10 3.4.2 Module mechanical items A Common Functional Module comprises: A cassette. A connector. An insert
48、ion extraction device. The volume of the cassette is delimited by a cuboid. The module is referenced against a Cartesian Reference System as represented on Figure 2. Volume for Insertion/ Extraction DeviceConnector Side BSide AModule HeaderSide DInsertion DirectionZXYGuide EdgeReference PlaneSide CF
49、igure 2 Module definitions prEN 4660-004:2009 (E) 11 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 from the Reference Plane to the module header (this excludes the Insertion Extraction Device and the connector). Mod
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