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1、INTEGRATED MODULAR AVIONICS PACKAGING AND INTERFACES ARINC SPECIFICATION 650 PUBLISHED: July 1, 1994 ANDOCUMENT Prepared by AIRLINES ELECTRONIC ENGINEERING COMMITTEE Published by AERONAUTICAL RADIO, INC. 2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401 Copyright 1994 by AERONAUTICAL RADIO, INC. 2551 Riva R
2、oad Annapolis, Maryland 21401-7465 USA ARINC SPECIFICATION 650 INTEGRATED MODULAR AVIONICS PACKAGING AND INTERFACES Published: July 1, 1994 Prepared by the Airlines Electronic Engineering Committee Specification 650Adopted by the Airlines Electronic Engineering Committee:April 13, 1994 Specification
3、 650Adopted by the Industry:July 1, 1994 -,-,- ARINC SPECIFICATION 650 TABLE OF CONTENTS ITEMSUBJECTPAGE 1.0INTRODUCTION1 1.1Purpose of this Document1 1.2Objectives1 1.3Scope1 1.4Principles1 1.5Nomenclature and Definitions1 1.5.1The Line Replaceable Module (LRM)1 1.5.2The Avionics Modular Unit (AMU)
4、1 1.5.3The Cabinet2 1.5.4LRM Guides2 1.5.4.1Ambient Air Interface2 1.5.5Electrical Interface2 1.5.5.1Electrical Power Supply2 1.5.6Wire Integration2 1.5.7Cooling Air2 1.5.8Environmental Considerations2 1.6Reference Documents2 2.0INTERCHANGEABILITY3 2.1Introduction3 2.1.1Connector Intermateability3 2
5、.1.2Connector Intermountability3 2.1.3Cabinet Interchangeability3 2.1.4Levels of Standardization3 3.0LINE REPLACEABLE MODULES (LRM)4 3.1Introduction4 3.2Form Factor and Case Dimensions4 3.2.1Datum and Method of Dimensioning4 3.2.2Front Panel Protrusions4 3.2.3Rear Panel Protrusions4 3.2.4LRM Backpla
6、te Deflection4 3.3Insertion/Extraction Device (IED)4 3.4Maximum Weight5 3.5Indexing5 3.5.1Indexing When Invertible LRMs are Used5 3.5.2LRM Mating Sequence5 3.6Cooling5 3.6.1Passive Cooling Augmentation5 3.7Power Dissipation6 3.8Electrical Interfaces6 3.9Electrical Bonding and Grounding6 3.10Standard
7、 LRM Environmental Conditions6 3.10.1Vibration, Shock and Acceleration6 3.10.1.1Random Vibration6 3.10.1.2Mechanical Shock7 3.10.2Thermal7 3.10.3Humidity7 3.10.4Contamination7 3.10.5Altitude7 3.10.6Electrostatic Discharge (ESD)7 3.10.7Power7 3.10.8Lightning8 3.10.9High Intensity Radiated Fields (HIR
8、F) Section4.0,Wire/Integration Backplane Assembly; Section 5.0, Cabinet Frame; etc.). Attachment 5 provides a table of the test categories and test procedures that should be followed to achieve the environmental performance necessary to meet certification requirements.The test conditions and procedu
9、res in Attachment5areextractedfromRTCADO-160, “Environmental Conditions and Test Procedures for Airborne Equipment“.Attachment 5 identifies both the conditions and limits together with the design parameters that need to be followed to achieve the environmental (including electromagnetic) requirement
10、s. Guidelines describing the methods recommended to achieve the design parameters are contained in ARINC Report 654. 1.6Reference Documents The latest version of the following documents are applicable to all equipment designed to meet this Specification: AECMA EN 2591, “Aerospace Series: Elements of
11、 Electricaland OpticalConnection TestMethods- General“ ANSIY14.5M-1982,“AmericanNationalStandard EngineeringDrawingsandRelatedDocumentation Practices.“ ARINC Specification 404A, “Air Transport Equipment Cases and Racking“ ARINC Specification 600, “Air Transport Avionics Equipment Interfaces“ ARINC R
12、eport 606, “Guidance for Electrostatic Sensitive Device Utilization and Protection“ ARINC Report 609, “Design Guidance for Aircraft Electrical Power Systems“ ARINC Report 651, “Design Guidance for Integrated Modular Avionics“ ARINCReport654,“EnvironmentalDesignGuidelinesfor Integrated Modular Avioni
13、cs“ EUROCAE ED-14, “Environmental Conditions and Test Procedures for Airborne Equipment“ FAR/JAR ATS 1000, “CFCs - Fire, Smoke, Toxicity, and Heat Release“ MIL-C-5809,“CircuitBreaker,Trip-free,Aircraft,General Specification For“ MIL-G-45204, “Gold Plating, Electrode Deposited“ MIL-H-5605, “Hydraulic
14、 Fluid, Petroleum Base, Aircraft, Missile, and Ordinance“ MIL-L-23699, “Lubricating Oil, Aircraft Turbine Engines, Synthetic Base, NATO Code Number 0-156“ MIL-STD-1344, “Test Methods for Electrical Connectors“ QQ-N-290, “Nickel Plating (Electrodeposited)“ RTCA Document DO-160, “Environmental Conditi
15、ons and Test Procedures for Airborne Equipment“ -,-,- ARINC SPECIFICATION 650 - Page 3 2.0 INTERCHANGEABILITY 2.1Introduction Any LRM fabricated to this specification should be mechanicallyinterchangeablewithanLRMperformingthe same function fabricated to this specification by another supplier.Cabine
16、tsshouldaccommodateany manufacturers LRM designed for a specific function. 2.1.1Connector Intermateability Inherent to the goals of ARINC Report 651, “Design Guidance for Integrated Modular Avionics“, is the concept that LRMs performing the same functions and fabricated from different manufacturers
17、be intermateable. For this goal to be successful, the cabinet plug connector should mate with the LRM receptacle connector with no modifications. The intent of this specification is to define the IMA connector to a level of detail so intermateability of the LRMs may be achieved. 2.1.2Connector Inter
18、mountability This specification defines the connector to a level of detail such that intermountability of the connector is achieved. 2.1.3Cabinet Interchangeability The mechanical, electrical, optical, and environmental interfaces between the cabinet and the LRM are controlled by this document. Howe
19、ver, cabinet assemblies designed for one aircraft are not necessarily interchangeable with cabinets in another aircraft. Cabinets are however expected to accommodate any manufacturers LRM with complete mechanical, electrical, optical, and environmental interface compatibility. COMMENTARY Cabinets wi
20、ll in most cases be custom designed to the available space in a particular aircraft and environment needs of the avionics. The design of the cabinets is thereforetheresponsibilityoftheairframe manufacturer.The cabinets should be designed to meet the general requirements discussed in Section 3.3. 2.1
21、.4Levels of Standardization Table 2-1 defines the level of standardization currently contained in this document for Size 2 connectors only. Size 1 connectors are dimensioned for reference and are not fully developed for standardization. The intent of this specification is that Size 1 connectors will
22、 also meet the level of standardization of Table 2-1 after they are fully developed. COMMENTARY It is a goal to specify full connector interchangeability, however, further experience with connector system development is necessary to determine whether this goalisachievable.Itisagoaltodevelop intercha
23、ngeability requirements for fiber optic termini. LEVEL OF STANDARDIZATION LRU ASSEMBL Y CONNECTOR ASSEMBLY SHELLINSERTCONTACTKEY IntermateableYesYesYes1YesYes IntermountableYesYesYes1Yes2Yes InterchangeableARINC 900YesYes2Yes2Yes NOTES:1.Including any non-removable contact installed in insert 2.Remo
24、vable contacts only Table 2-1 Level of Standardization ARINC SPECIFICATION 650 - Page 4 3.0 LINE REPLACEABLE MODULES (LRM) 3.1 Introduction The Line Replaceable Module is the basic unit of the Integrated Modular Avionics (IMA) concept. LRMs can be categorized by the following functions:power supplie
25、s, processors, digital bus terminals, signal I/O, etc. Those various functions may require different module envelopesizesanddifferentconnectorinsertarrangements. This Specification provides the interfaces between the module,theelectricalwiringanddatabuses,the environment and supporting structure pro
26、vided by the cabinet assemblies. The general arrangement of a generic cabinet assembly is shown in Attachment 1. Internal configuration of the modules is the responsibility of the LRM supplier. In addition to the interfaces which are needed for interchangeability, precautions in the following sectio
27、ns should be observed in the internal design of the avionics. This specification allows for the possibility that LRMs (modules) can be designed for operation in an inverted position within a cabinet. COMMENTARY Acabinetarchitecturewhichfeaturesmultiple computation channels with a growth area uncommi
28、tted to a particular channel can derive a benefit when certain LRMs can be mated in either of two orientations. 3.2 Form Factor and Case Dimensions The module is a right parallelepiped.The height and length dimensions are fixed.Variations in LRM sizes (volume) are accounted for by width.Ten widths a
29、re defined in this Specification.The smallest LRM is designated as 1 Avionics Modular Unit (AMU) and others are designated nAMU. An LRM width is nominally given by the equation: 0.7 + 0.4 (AMU) inches. The LRM case dimensions are detailed in Attachment 2. 3.2.1Datum and Method of Dimensioning Dimens
30、ioning control is established by use of datums which are physical features from which other locations can be measured. Datums are shown in Attachment 2. 3.2.2Front Panel Protrusions All protrusions, such as the IED, carrying handles, switches, test connectors, and indicators should remain within the
31、 outline envelope shown in Attachment 3 when in a retained and actuated position. 3.2.3Rear Panel Protrusions The primary purpose of the rear of the module is to accommodate the electrical connector.Any other use should not interfere with the interfacing of the LRM with the cabinet assembly. Connect
32、or mounting screw heads should lie within limits depicted in Attachment 4. Factors limiting the rear panel protrusion are the connector flange thickness, EMI gasket, and screwheads.See Attachment 2. 3.2.4LRM Backplate Deflection The backplate deflection during the period when the LRM is being instal
33、led, or is being removed from the cabinet assembly should be within the dimensions specified in Attachment 2. 3.3 Insertion/Extraction Device (IED) The Insertion/Extraction Device (IED) should provide a means of inserting the LRM into the cabinet and extracting the LRM from the cabinet. Upon inserti
34、on, the IED should provide the force necessary to mate the LRM connector receptacle to the cabinet connector plug, and upon extraction, the IED should provide the force necessary to separate the receptacle from the plug. The LRM should be inserted and extracted by a single action mechanism which sim
35、ultaneously reacts against the clevis pins and which is located within the space envelope shown in Attachment 3. Additional requirements of the IED are as follows: a.Insertion and extraction of an LRM should be accomplished by use of the IED and be a single- handed operation. In the fully open posit
36、ion, the IED should not protrude beyond the volume 8.2 inches in the Z dimension, 8.2 inches in the Y dimension, and W in the X dimension, with the origin of the X-Y-Z coordinates at the lower left corner of the LRM front face-plate (or a point determined by the intersection of the projection of the
37、 lower most point on the bottom of the face plate and furthest left protrusion on the left side of the face plate) and X, Y, and Z defined as shown in Attachment 1. b.The IED cams should engage compensating keepers contained in the cabinet which apply a longitudinal force of 175 pounds minimum and 2
38、25 pounds maximum on the front face of the LRM. This force acts to maintain the LRM and cabinet connector halves in a fully mated position during shock and vibration. c.The nominal linear travel of the compensating keepers in the cabinet should be 0.300 inches. d.The IED (including the compensating
39、keepers) should not require adjustment during installation or normal operationsforLRMinstallation,retention,and removal. e.The maximum force required to operate the IED should not exceed 20 pounds. f.The IED should lock in the fully engaged position. The cabinet frame should guide the LRM to ensure
40、positioning within the 0.100 inch radial misalignment acceptance range of the connector alignment device. ARINC SPECIFICATION 650 - Page 5 3.0 LINE REPLACEABLE MODULES (LRM) (contd) g.The IED should not be a safety hazard. h.The IED should be capable of exerting the forces involved without damage or
41、 permanent deformation. i.The IED should not show any signs of degradation of functionality after 1000 mating/unmating cycles at a rate not to exceed ten cycles per minute. j.The IED should accommodate and survive the LRM environmental requirements set forth in Attachment 5 while maintaining the LRM
42、 connector receptacle and cabinet connector plug in a fully mated condition. k.The IED should be capable of inserting, extracting, and retaining the LRMs in the cabinet in an upright position and in a position 180 degrees from that position (an inverted position). l.The IED should be positioned on t
43、he front panel along the centerline of the connector. m. The IED should meet the dimensional requirements shown in Attachments 2 and 3. n.The IED and all associated hardware fastened to the cabinet, such as the compensating keeper assembly, should not extend beyond the width of a Size 1 AMU LRM. o.H
44、ardware associated with the IED which is contained in the cabinet, such as the compensating keeper assembly, should not extend beyond the volume constraints shown in Attachment 2 and should not restrict more than 50% of the air to pass unobstructed through this volume. p.The compensating keeper shou
45、ld not bind or gall on the cabinet assembly in such a way as to prevent the IED from performing to the requirements shown in this specification. q.The force that the IED exerts on the LRM during and after insertion into the cabinet should be as shown in Attachment 3.Insertion of the LRM should be pr
46、evented if the connector alignment device is not properly engaged.The insertion mechanism should provide a positive indication when the connector is fully seated. The indication may be aural, visual, or tactile means. 3.4 Maximum Weight LRM maximum weight limits are shown in Attachment 2. These enab
47、le adequate structural design of the cabinet assembly which should transfer static and dynamic loads to the airframe structure. 3.5 Indexing To prevent LRMs from being inadvertently placed in the wrong cabinet location, a standard means to index all LRMs should be provided.The indexing should be an
48、integral part of the connector as described in Attachment 4. 3.5.1Indexing When Invertible LRMs are Used When it is desired to use invertible LRMs, a symmetrical connector keying position should be used.LRMs of different types should use different connector keying positions.The guide pins at the fro
49、nt of LRMs of different types should be located in different positions to provide additional protection against incorrect installation. 3.5.2LRM Mating Sequence The following list is the LRM mating order of sequence: a.Shell Guide Pins b.Shell Housing c.Keying Pins d.Front Guide Pins e.IED f.Ground/Safety Contacts g.Signal Ground/Data/Control Signals/Power Contacts The LRM mating sequence and connector construction should provide a method of discharging ESD voltage from theLRMcasepriortotheengagementofth