ARINC 601-1981 Control Display Interfaces《控制或显示器接口》.pdf

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1、 CONTROL/DISPLAY INTERFACESARINC SPECIFICATION 601PUBLISHED: FEBRUARY 10, 1981AN DOCUMENTPrepared byAIRLINES ELECTRONIC ENGINEERING COMMITTEEPublished byAERONAUTICAL RADIO, INC.2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401This document is based on material submitted by variousparticipants during the dra

2、fting process. Neither AEEC norARINC has made any determination whether these materialscould be subject to valid claims of patent, copyright or otherproprietary rights by third parties, and no representation orwarranty, express or implied, is made in this regard. Any use ofor reliance on this docume

3、nt shall constitute an acceptancethereof “as is” and be subject to this disclaimer.Copyright 1998 byAERONAUTICAL RADIO, INC.2551 Riva RoadAnnapolis, Maryland 21401-7465 USAARINC SPECIFICATION 601 CONTROL/DISPLAY INTERFACESPublished: February 10, 1981Prepared by the Airlines Electronic Engineering Co

4、mmitteeSpecification 601 Adopted by the Airlines Electronic Engineering Committee: August 31, 1979iiFOREWORDActivities of AERONAUTICAL RADIO, INC. (ARINC)and thePurpose of ARINC Reports and SpecificationsAeronautical Radio, Inc., is a corporation in which the United States scheduled airlines are the

5、 principalstockholders. Other stockholders include a variety of other air transport companies, aircraft manufacturers and non-U.S.airlines.Activities of ARINC include the operation of an extensive system of domestic and overseas aeronautical landradio stations, the fulfillment of systems requirement

6、s to accomplish ground and airborne compatibility, the allocationand assignment of frequencies to meet those needs, the coordination incident to standard airborne communications andelectronics systems and the exchange of technical information. ARINC sponsors the Airlines Electronic EngineeringCommit

7、tee (AEEC), composed of airline technical personnel. The AEEC formulates standards for electronic equipmentand systems for the airlines. The establishment of Equipment Characteristics is a principal function of this Committee.It is desirable to reference certain general ARINC Specifications or Repor

8、ts which are applicable to more thanone type of equipment. These general Specifications or Reports may be considered as supplementary to the EquipmentCharacteristics in which they are referenced. They are intended to set forth the desires of the airlines pertaining tocomponents and general design, c

9、onstruction and test criteria, in order to insure satisfactory operation and the necessaryinterchangeability in airline service. The release of a Specification or Equipment Characteristic should not be construedto obligate ARINC or any airline insofar as the purchase of any components or equipment i

10、s concerned.An ARINC Report (Specification or Characteri stic) has a twofold purpose, which is:(1) To indicate to the prospective manufacturers of airline electronic equipment the considered opinion of theairline technical people coordinated on an industry basis concerning requisites of new equipmen

11、t, and(2) To channel new equipment designs in a direction which can result in the maximum possible standardizationof those physical and electrical characteristics which influence interchangeability of equipment withoutseriously hampering engineering initiative.iiiPREFACETOARINC SPECIFICATION 601Sinc

12、e 1970 a great deal of work has been put forth by ARINC, Airlines, Airframe manufacturers, and avionics suppliersto upgrade existing documents which control avionics thermal characteristics. This effort was justified by theincreasingly apparent inverse relationships between equipment operating tempe

13、rature and reliability levels.This same awareness led to the development and publication of the new avionics equipment interface document “ARINCSPECIFICATION 600.”With the other new and revised ARINC Specifications (600, 404A and 408A) the majority of traditionally active radioswere covered. Current

14、 trends in electronics however, have made it necessary to develop this additional Specification.The trends involved are the new CRT Displays and the trend for active electronic circuitry to be encased in whattraditionally has been control boxes with passive components only.Recognizing the changing d

15、esign philosophy as well as state-of-the-art changes, it was considered advisable to generatethis additional Specification which is intended to include all flight deck electronics not currently included in ARINC404A, 408A, or 600. Specifically included are:+ Glare shield area+ Overhead panel area+ S

16、ide panel area+ Pedestal+ Instrument Panel (those equipment not covered by ARINC 408A)+ Flight Engineers ConsoleThere is no intent implicit in the issuance of this ARINC Specification to deprecate or derogate any existing ARINCSpecification. This Specification is expected to fill the need for standa

17、rds of thermal design for those equipments whereexisting Specifications are not applicable.REFERENCES1. ARINC Specification 404A, “Air Transport Equipment Cases and Racking”.2. ARINC Specification 408A, “Air Transport Indicator Cases and Mounting”.3. ARINC Specification 600 “Air Transport Avionics E

18、quipment Interfaces”.4. Radio Technical Commission for Aeronautics Document Number DO-160 “Environmental Conditions and TestProcedures for Airborne Electronic/Electrical Equipment and Instruments”/EUROCAE ED-14.5. Military Standard MS25212(ASG), “Control Panel, Console Type, Aircraft Equipment Basic

19、 Dimensions”.6. International Standard ISO 1000 “S.I. Units and Recommendations for the Use of Their Multiples and of CertainOther Units.”ivARINC SPECIFICATION 601TABLE OF CONTENTSITEM SUBJECT PAGE1.0 GENERAL CONSIDERATIONS 11.1 Objective 11.2 Installation Locations 11.2.1 Instrument Panel Mounted E

20、quipment 11.2.2 Pedestal Mounted Equipment 11.2.3 Glare Shield and Side Panel Mounted Equipment 1-21.2.4 Overhead and Flight Engineers Panels 21.3 Cooling Air Ducts and Plenums 21.4 Standard International (S.I.) Units 21.5 LRU Interchangeability 21.6 Installation Standards 21.7 Relationship of Cooli

21、ng Philosophies 2-32.0 BASIC DESIGN STANDARDS 42.1 Cooling Medium 42.2 Three Categories of Cooling 42.3 Thermal Dissipation Limits (Maximums) 4-52.4 Surface Temperature Limits 52.4.1 Face Temperature 52.4.2 Control Surface Temperatures 52.4.3 Case Temperature Limits (Type A Equipment Only) 52.4.4 Ho

22、t Spot Case Temperature (Type B Equipment Only) 52.5 Coolant Air Flow Rate 52.5.1 Flow-Through (Type A) Cooling 52.5.2 Flow-By (Type B) Cooling 62.6 Air Pressure Drop Through Type A Equipment 62.7 Coolant Air Quality and Management 62.7.1 General 62.7.2 Air Filters 6-72.7.3 Particle Size 72.8 Coolan

23、t Air Temperature (Types A and B) 72.9 Coolant Air Relative Humidity 72.10 Ambient Air Temperature (Type C Equipment) 72.11 Design Verification 72.12 Tray Mounting Form Factor 7-82.12.1 Basic Form Factors 82.12.2 Holddown/Extractor/Handle 82.13 Cooling Air Interface 82.13.1 Minimum Hose/Duct Sizes 8

24、2.13.2 Panel Mounted Displays 82.13.3 Standard for DZUS Mounted CDU (Type A) 82.13.4 Foreign Object Screen 83.0 DESIGN CRITERIA AND GUIDANCE 93.1 General 93.2 Mounting Areas 93.2.1 Instrument Panel Mounted Equipment 93.2.2 Pedestal Mounted Units 93.2.3 Other Mounting Area 93.3 Protrusions on the Cas

25、e 93.4 Coolant Air Leakage from the Equipment 93.5 Electronic Design 93.5.1 Equipment Component Parts Application 93.5.2 Thermal (Internal Survey) 9-103.5.3 Abnormal Operation 103.6 Airplane Cooling Provisions 103.6.1 General 103.6.2 Abnormal In-Flight Operation 103.6.3 Indication of Airflow 103.6.4

26、 Supplemental Cooling 103.7 Acoustic Noise 11NEXT PAGE INTENTIONALLY LEFT BLANKvTABLE OF CONTENTS (contd)ITEM SUBJECT PAGE4.0 APPRAISAL COOLING 124.1 Cooling and Thermal Appraisal 124.2 Cooling Interfaces 124.3 Equipment Design Limits 124.4 Reference Surface Temperature (All Equipment) 124.5 Equipme

27、nt Thermal Appraisal 124.5.1 Equipment Thermal Analysis 134.5.2 Identification and Data Tabulation for Heat Dissipating and Temperature 13Critical Parts4.6 Thermal Information 13ATTACHMENTS1 Summary of Cooling Limits and Applications 142 Form Factor For Pedestal Mounted Units 153 Typical Tray Mounte

28、d Form Factor 164 CDU Holddown/Extractor Handle 175-1 Standard Flow-Through Cooling for MS25212 (DZUS) Mounted Units 18(Large Units)5-2 Standard Flow-Through Cooling for MS25212 (DZUS) Mounted Units 19(Small Units)6 Air Connection Interface 207 Temperature Limit for Control Surfaces 218.0 Notes for

29、Attachment 8-1 Through 8-3 228-1 Test Parameters for Type A Cooling (Flow-Through) 238-2 Test Parameters for Type B Cooling (Flow-By) 248-3 Test Parameters for Type C Cooling (No Cooling) 259 Cooling Evaluation Test 26-4010 Maximum Case Temperature 4111 Optional Flow-By Cooling For MS25212 (DZUS) Mo

30、unted Units 42APPENDICES1 Bibliography of the ARINC 601 Control/Display Interfaces Project 43ARINC SPECIFICATION 601 - Page 11.0 GENERAL CONSIDERATIONSARINC 601 is intended to take advantage of technicaland procedural advancements that were not available tothose who developed ARINC 408/408A in provi

31、dingthermal design guidance for the avionic units and theirinstallation in the flight deck area of transport aircraft.Earlier industry packaging developments evolved into theindicator cases and mounting boxes which have beencovered by ARINC Specification 408 since 1960.Present industry experience ha

32、s demonstrated the needfor new concepts to avoid problems resulting from thegrowing complexity of avionic control and displayequipment.COMMENTARYARINC 408A is not superseded by this document,but rather, supplemented by it. There will continueto be avionic indicators best serviced by ARINC408A after

33、ARINC 601 is issued. Section 1.7provides further information on the relationshipsbetween these documents.1.1 ObjectiveThe objective of this document is to provide a system forthe effective control of the environment for avionicequipment. This includes:A. BASIC DESIGN STANDARDS for avionicequipment a

34、nd its installation to assure suitablethermal interfaces (Chapter 2).B. DESIGN CRITERIA AND GUIDANCE TOprovide further details concerning the equipmentand installations (Chapter 3).C. COOLING APPRAISAL to provide data whichshould be utilized by users or equipment andaircraft manufacturers to confirm

35、 the equipmentthermal design and to show compatibility withaircraft environment (Chapter 4).Inherent in this objective is the principle that failure ofthe LRU resulting from the mechanical, electrical andenvironmental interfaces encountered on the aircraft canbe minimized and that aircraft providing

36、 the interfaces asstated herein should not be held responsible for failures ofthis nature.COMMENTARYThis Specification is provided for use by thecommercial air transport industry, the airlineoperators, the airframe manufacturers and theequipment manufacturers. The AEEC Subcom-mittees on systems and

37、subsystems should adhere tothe guidance provided herein when creatingCharacteristics for new systems. Military andgeneral aviation organizations are also encouragedto utilize this Specification, where appropriate, fortheir aircraft avionic equipment and installations.1.2 Installation Locations1.2.1

38、Instrument Panel Mounted EquipmentThree types of equipment other than instrumentsfrequently are installed in the instrument panels ofaircraft: Control, Display and combined Control/Displayunits. These equipments are included in that the thermalcharacteristics are specified but the electrical interfa

39、cesare not. In addition, recent developments have addedCRT Instruments as a new equipment in the instrumentpanel area. CRT Instrument mechanical and thermalinterface needs are covered herein.COMMENTARYThe control and display units which are designedinto the instrument panel historically have beenuni

40、que to the aircraft in most instances. For thisreason it is considered that the standardization,where considered by the users to be necessary, willbe covered in the ARINC EquipmentCharacteristics for the particular system.Electronic flight and engine instruments (CRTInstruments) are considered to be

41、 common to manyaircraft for the future and therefore require standardtray mounting form factor considerations as well ascontrolled thermal characteristics.The mechanical characteristics for CRT instrumentcases are described in Section 2.12.1.2.2 Pedestal Mounted EquipmentThis Specification describes

42、 the standard mechanical andthermal interfaces between the aircraft pedestal and theequipment. The Military Standard MS25212 (DZUS)form factor and mechanical interfaces, as shown inAttachment 2, are normally used for pedestal mountedequipment. The equipment thermal interface described inSection 2 of

43、 this document applies to all pedestalmounted equipment. The configuration of all pedestalmounted equipment should conform to the MS25212DZUS mounting described in Section 3.2.2.COMMENTARYThe use of the pedestal area for simple controls hasbeen traditional on commercial aircraft. Recently,however, m

44、ore active electronic circuitry has beenincluded in control units. The increased thermaldissipation has resulted in increased operatingtemperatures and decreased reliability. It is theintent of this document to provide the coolingstandards needed to assure an optimum reliabilitylevel without imposin

45、g undue design limits.1.2.3 Glare Shield and Side Panel MountedEquipmentControls and displays mounted in the Glare Shield andSide Panels traditionally have been unique designs foreach aircraft configuration. This document does notdefine the mechanical interface, but guidance is providedfor cooling t

46、hese units.ARINC SPECIFICATION 601 - Page 21.0 GENERAL CONSIDERATIONS (contd)1.2.3 Glare Shield and Side Panel Mounted Equip-ment (contd)COMMENTARYSince the equipment normally installed in theseareas is usually considered unique to the aircraftdesign, it is not logical to require standardization ofm

47、echanical configuration or electrical interface.From a thermal standpoint, however, there is asmuch to gain from proper cooling on equipment inthese areas as for equipment in the radio rack orinstrument panel.1.2.4 Overhead and Flight Engineers PanelsUnits used in the overhead and Flight Engineers p

48、anelstraditionally have used the Military Standard MS25212(DZUS) form factor and some type of passive cooling.This document uses the DZUS mechanical interface anddefines three categories of cooling.1.3 Cooling Air Ducts and PlenumsDucting and plenums should be provided as an integralpart of the airc

49、raft equipment mounting, or on adjacentstructure, to direct the flow of cooling air through oraround the LRU. Apertures are defined for each LRU toprovide for passage of the cooling air through the unitwhere flow-through cooling is provided.1.4 Standard International (S.I.) UnitsMost parameters are expressed in “English” units with theequivalent Standard International (S.I.) units.COMMENTARYThe need to retain compatibility with ARINC 408Adimensions and tolerances dictates the use of theestablished “English” units in this document.However, other parameters, such as temperature and