ARINC-650-1994.pdf
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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
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