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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 Aeronautical Radio Inc. Provided by IHS unde
2、r license with ARINC Licensee=IHS Employees/1111111001, User=Japan, IHS Not for Resale, 08/04/2008 01:12:00 MDTNo reproduction or networking permitted without license from IHS -,-,- Copyright 1994 by AERONAUTICAL RADIO, INC. 2551 Riva Road Annapolis, Maryland 21401-7465 USA ARINC SPECIFICATION 650 I
3、NTEGRATED 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 650Adopted by the Industry:July 1, 1994 Copyright Aeronautical
4、Radio Inc. Provided by IHS under license with ARINC Licensee=IHS Employees/1111111001, User=Japan, IHS Not for Resale, 08/04/2008 01:12:00 MDTNo reproduction or networking permitted without license from IHS -,-,- ARINC SPECIFICATION 650 TABLE OF CONTENTS ITEMSUBJECTPAGE 1.0INTRODUCTION1 1.1Purpose o
5、f 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)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 1.5.6Wir
6、e Integration2 1.5.7Cooling Air2 1.5.8Environmental Considerations2 1.6Reference Documents2 2.0INTERCHANGEABILITY3 2.1Introduction3 2.1.1Connector Intermateability3 2.1.2Connector Intermountability3 2.1.3Cabinet Interchangeability3 2.1.4Levels of Standardization3 3.0LINE REPLACEABLE MODULES (LRM)4 3
7、.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 Backplate Deflection4 3.3Insertion/Extraction Device (IED)4 3.4Maximum Weight5 3.5Indexing5 3.5.1Indexing When Invertible LRMs are Used5 3.5.
8、2LRM Mating Sequence5 3.6Cooling5 3.6.1Passive Cooling Augmentation5 3.7Power Dissipation6 3.8Electrical Interfaces6 3.9Electrical Bonding and Grounding6 3.10Standard LRM Environmental Conditions6 3.10.1Vibration, Shock and Acceleration6 3.10.1.1Random Vibration6 3.10.1.2Mechanical Shock7 3.10.2Ther
9、mal7 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 (HIRF) Section4.0,Wire/Integration Backplane Assembly; Section 5.0, Cabinet Frame; etc.). Attachment 5 provides a table of the test catego
10、ries and test procedures that should be followed to achieve the environmental performance necessary to meet certification requirements.The test conditions and procedures in Attachment5areextractedfromRTCADO-160, “Environmental Conditions and Test Procedures for Airborne Equipment“.Attachment 5 ident
11、ifies both the conditions and limits together with the design parameters that need to be followed to achieve the environmental (including electromagnetic) requirements. Guidelines describing the methods recommended to achieve the design parameters are contained in ARINC Report 654. 1.6Reference Docu
12、ments The latest version of the following documents are applicable to all equipment designed to meet this Specification: AECMA EN 2591, “Aerospace Series: Elements of Electricaland OpticalConnection TestMethods- General“ ANSIY14.5M-1982,“AmericanNationalStandard EngineeringDrawingsandRelatedDocument
13、ation Practices.“ ARINC Specification 404A, “Air Transport Equipment Cases and Racking“ ARINC Specification 600, “Air Transport Avionics Equipment Interfaces“ ARINC Report 606, “Guidance for Electrostatic Sensitive Device Utilization and Protection“ ARINC Report 609, “Design Guidance for Aircraft El
14、ectrical Power Systems“ ARINC Report 651, “Design Guidance for Integrated Modular Avionics“ ARINCReport654,“EnvironmentalDesignGuidelinesfor Integrated Modular Avionics“ EUROCAE ED-14, “Environmental Conditions and Test Procedures for Airborne Equipment“ FAR/JAR ATS 1000, “CFCs - Fire, Smoke, Toxici
15、ty, and Heat Release“ MIL-C-5809,“CircuitBreaker,Trip-free,Aircraft,General Specification For“ MIL-G-45204, “Gold Plating, Electrode Deposited“ MIL-H-5605, “Hydraulic Fluid, Petroleum Base, Aircraft, Missile, and Ordinance“ MIL-L-23699, “Lubricating Oil, Aircraft Turbine Engines, Synthetic Base, NAT
16、O Code Number 0-156“ MIL-STD-1344, “Test Methods for Electrical Connectors“ QQ-N-290, “Nickel Plating (Electrodeposited)“ RTCA Document DO-160, “Environmental Conditions and Test Procedures for Airborne Equipment“ Copyright Aeronautical Radio Inc. Provided by IHS under license with ARINC Licensee=IH
17、S Employees/1111111001, User=Japan, IHS Not for Resale, 08/04/2008 01:12:00 MDTNo reproduction or networking permitted without license from IHS -,-,- ARINC SPECIFICATION 650 - Page 3 2.0 INTERCHANGEABILITY 2.1Introduction Any LRM fabricated to this specification should be mechanicallyinterchangeable
18、withanLRMperformingthe same function fabricated to this specification by another supplier.Cabinetsshouldaccommodateany 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
19、the concept that LRMs performing the same functions and fabricated from different manufacturers 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 conn
20、ector to a level of detail so intermateability of the LRMs may be achieved. 2.1.2Connector Intermountability 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, an
21、d environmental interfaces between the cabinet and the LRM are controlled by this document. However, 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 me
22、chanical, electrical, optical, and environmental interface compatibility. COMMENTARY Cabinets will 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 manufacture
23、r.The cabinets should be designed to meet the general requirements discussed in Section 3.3. 2.1.4Levels 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 full
24、y developed for standardization. The intent of this specification is that Size 1 connectors will 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
25、 development is necessary to determine whether this goalisachievable.Itisagoaltodevelop interchangeability requirements for fiber optic termini. LEVEL OF STANDARDIZATION LRU ASSEMBL Y CONNECTOR ASSEMBLY SHELLINSERTCONTACTKEY IntermateableYesYesYes1YesYes IntermountableYesYesYes1Yes2Yes Interchangeab
26、leARINC 900YesYes2Yes2Yes NOTES:1.Including any non-removable contact installed in insert 2.Removable contacts only Table 2-1 Level of Standardization Copyright Aeronautical Radio Inc. Provided by IHS under license with ARINC Licensee=IHS Employees/1111111001, User=Japan, IHS Not for Resale, 08/04/2
27、008 01:12:00 MDTNo reproduction or networking permitted without license from IHS -,-,- 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 f
28、ollowing functions:power supplies, 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 environm
29、ent and supporting structure provided 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, pre
30、cautions in the following sections 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 cha
31、nnels with a growth area uncommitted 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 acc
32、ounted for by width.Ten widths are 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 a
33、nd Method of Dimensioning Dimensioning 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 ind
34、icators should remain within the 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 wi
35、th the cabinet assembly. Connector 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 per
36、iod when the LRM is being installed, 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 LR
37、M from the cabinet. Upon insertion, 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 s
38、ingle action mechanism which simultaneously 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 op
39、eration. In the fully open position, 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 inter
40、section of the projection of the 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 f
41、orce of 175 pounds minimum and 225 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
42、IED (including the compensating 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
43、 should guide the LRM to ensure positioning within the 0.100 inch radial misalignment acceptance range of the connector alignment device. Copyright Aeronautical Radio Inc. Provided by IHS under license with ARINC Licensee=IHS Employees/1111111001, User=Japan, IHS Not for Resale, 08/04/2008 01:12:00
44、MDTNo reproduction or networking permitted without license from IHS -,-,- 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 permanent deformation. i.The IE
45、D 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 connector receptacle and cabine
46、t 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 the front panel along the centerl
47、ine 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.Hardware associated with the IED
48、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 should not bind or gall on the cabin
49、et 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 prevented if the connector alignment device is not properly engaged.The insertion mechanism should provi