ARINC 727-1-1987 Airborne Microwave Landing System《空中传播微波着陆系统1979包括附录1》.pdf

1、 AIRBORNE MICROWAVE LANDINGSYSTEMARINC CHARACTERISTIC 727-1PUBLISHED: AUGUST 27, 1987AN DOCUMENTPrepared byAIRLINES ELECTRONIC ENGINEERING COMMITTEEPublished byAERONAUTICAL RADIO, INC.2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401Copyright 1998 byAERONAUTICAL RADIO, INC.2551 Riva RoadAnnapolis, Maryland

2、24101-7465 USAARINC CHARACTERISTIC 727-1 AIRBORNE MICROWAVE LANDING SYSTEMPublished: August 27, 1987Prepared by the Airlines Electronic Engineering CommitteeCharacteristic 727 Adopted by the Airlines Electronic Committee: August 31, 1979Characteristic 727 Adopted by Industry: November 16, 1979Charac

3、teristic 727-1 Adopted by the Airlines Electronic Engineering Committee: January 31, 1987FOREWORDActivities of AERONAUTICAL RADIO, INC. (ARINC)and thePurpose of ARINC CharacteristicsAeronautical Radio, Inc. is a corporation in which the United States scheduled airlines are theprincipal stockholders.

4、 Other stockholders include a variety of other air transport companies, aircraftmanufacturers and foreign flag airlines.Activities of ARINC include the operation of an extensive system of domestic and overseasaeronautical land radio stations, the fulfillment of systems requirements to accomplish gro

5、und andairborne compatibility, the allocation and assignment of frequencies to meet those needs, thecoordination incident to standard airborne communications and electronics systems and the exchangeof technical information. ARINC sponsors the Airlines Electronic Engineering Committee (AEEC),composed

6、 of airline technical personnel. The AEEC formulates standards for electronic equipmentand systems for the airlines. The establishment of Equipment Characteristics is a principal functionof this Committee.An ARINC Equipment Characteristic is finalized after investigation and coordination withthe air

7、lines who have a requirement or anticipate a requirement, with other aircraft operators, withthe Military services having similar requirements, and with the equipment manufacturers. It isreleased as an ARINC Equipment Characteristic only when the interested airline companies are ingeneral agreement.

8、 Such a release does not commit any airline or ARINC to purchase equipment sodescribed nor does it establish or indicate recognition of the existence of an operational requirementfor such equipment, nor does it constitute endorsement of any manufacturers product designed orbuilt to meet the Characte

9、ristic. An ARINC Characteristic has a twofold purpose, which is:(1) To indicate to the prospective manufacturers of airline electronic equipment theconsidered opinion of the airline technical people, coordinated on an industry basis,concerning requisites of new equipment, and(2) To channel new equip

10、ment designs in a direction which can result in the maximumpossible standardization of those physical and electrical characteristics whichinfluence interchangeability of equipment without seriously hampering engineeringinitiative.iiTABLE OF CONTENTSiiiTITLE SUBJECT PAGE1.0 INTRODUCTION AND DESCRIPTI

11、ON 11.1 Purpose of This Characteristic 11.2 Function of the Equipment 11.3 Unit Description 11.3.1 MLS Receiver Processor Unit 11.3.2 Frequency Control 11.3.3 Antennas 11.3.4 Instrumentation 11.4 Interchangeability 11.4.1 General 11.4.2 Interchangeability Desired for the ARINC 727 MLS Receiver Compo

12、nents 11.4.3 “Generation Interchangeability” Considerations 1-21.5 Regulatory Approval 22.0 INTERCHANGEABILITY STANDARDS 32.1 Introduction 32.2 Form Factors, Connectors & Index Pin Coding 32.2.1 MLS Receiver Processor Unit 32.2.2 Standard Control Panel 32.2.3 Indicators 32.2.4 Antennas 32.3 Standard

13、 Interwiring 32.4 Power Circuitry 42.4.1 Primary Power Input 42.4.2 Power Control Circuitry 42.4.3 The AC Common Cold 42.4.4 The Common Ground 42.5 Standardized Signaling 42.5.1 ARINC 429 DITS Data Bus 42.5.2 Standard “Open” 42.5.3 Standard “Ground” 52.5.4 Standard “Applied Voltage” Output 52.5.5 St

14、andard Discrete Input 52.5.6 Standard Discrete Output 52.6 Environmental Conditions 52.7 Cooling 5-62.8 Grounding and Bonding 63.0 MLS RECEIVER PROCESSOR DESIGN 73.1 MLS Receiver Processor 73.1.1 Signal Validity 73.1.2 Frequency Range and Channeling 73.1.3 Receiver Processor Sensitivity 73.1.4 Frequ

15、ency Stability 73.1.5 In-Band Interference 7-83.1.6 Out-of-Band Interference 83.1.7 The DME Connection 83.1.8 Monitor Integrity 83.1.9 Functional Test 83.2 Digital Data Inputs 83.2.1 Channel Selection 93.2.2 Centralized Fault Display System Input 93.2.3 DME Inputs 93.3 Digital Data Outputs 93.3.1 Se

16、lected Channel and Angle Reporting 93.3.2 Deviation Outputs 9-103.3.3 Basic and Auxiliary Data Outputs 103.3.4 Discrete Word Outputs 103.3.5 BITE Outputs 103.3.6 Identification Output 103.4 Analog Outputs 103.4.1 Deviation Signal Output Characteristics 103.4.2 AFCS Outputs 10-113.4.3 High Level Outp

17、uts 113.4.4 Low Level Outputs 113.4.5 Deviation Output Polarity 11-123.4.6 Deviation Output Sensitivity 123.4.6.1 High Level Deviation Output Sensitivity 123.4.6.2 Low Level Deviation Output Sensitivity 12TABLE OF CONTENTS (contd)ivTITLE SUBJECT PAGE3.4.7 Course Stability 123.4.7.1 Azimuth Course Ce

18、ntering Stability 123.4.7.2 Glide Path Course Centering Stability 133.4.8 Course Accuracy 133.4.8.1 Path Follow Error 133.4.8.2 Control Motion Noise 133.4.8.3 Bias Error 143.4.8.4 Resolution 143.4.9 Deviation Output Linearity 143.4.9.1 Azimuth Course Deviation Output Linearity 143.4.9.2 Glide Path C

19、ourse Deviation Output Linearity 143.4.10 Deviation Output Damping 143.5 Warning Signals 143.5.1 Warning Signal Characteristics 153.5.1.1 Digital Data Word Warnings 153.5.1.2 AFCS Warning Signals 153.5.1.3 High Level Instrument Warning Signals 153.5.1.4 Low Level Instrument Warning Signals 153.5.1.5

20、 Glide Slope Deviation Bar and Flag Biasing 153.5.2 Warning Conditions 153.5.2.1 Equipment Failure 15-163.5.2.2 Loss of Input Signal 163.5.2.3 Ground Station Not Available 163.5.2.4 Inadequate Receipt or Decoding of Data 16-173.5.2.5 Command Conflicts 173.6 Discrete Inputs 17-183.7 Output Discretes

21、18-193.8 Program Functions 193.9 Audio Output 193.9.1 Audio Output Power 193.9.2 Audio Source Impedance 193.9.3 Audio Output Level Variation with Load Impedance 193.9.4 Audio Output Service Adjustment 19-203.10 AC Power Output to CDU 203.11 DC Power Output to Preamplifier 203.12 MIL-STD-1553B 204.0

22、CONTROL DISPLAY UNIT 214.1 Control Functions 214.1.1 Auto/Manual 214.1.2 Channel Selection 214.1.3 Approach Azimuth Angle Select 224.1.4 Glide Path Angle Select 224.1.5 Back Azimuth Angle Select 224.1.6 Self-Test 224.2 Display Functions 224.2.1 Approach Azimuth Magnetic Course Selected 224.2.2 Glide

23、 Path Angle Selected 224.2.3 Back Azimuth Magnetic Course Selected 224.2.4 Display Options 22-234.3 Annunciation and Warning 234.3.1 In-Test Annunciation 234.3.2 Approach/Back Azimuth 234.3.3 MLS Fault 234.3.4 Select Warning 234.4 Panel Illumination 235.0 ANTENNAS 245.1 Antenna Configurations 245.2

24、Antenna Characteristics 245.3 Installation Considerations 245.4 Antenna Design 245.5 Antenna Preamplifier 24-255.6 Power Divider Module Characteristics 256.0 PROVISIONS FOR AUTOMATIC TEST EQUIPMENT 266.1 General 266.2 Unit Identification 26TABLE OF CONTENTS (contd)vTITLE SUBJECT PAGE7.0 BUILT-IN TES

25、T EQUIPMENT (BITE) 277.1 Built-In Test Equipment 277.2 BITE Display 277.3 Fault Monitor 277.4 Self-Test 287.5 Monitor Memory Output 288.0 Definitions 29-30ATTACHMENTS1 Connector Positioning 312 ARINC 727 MLS Standard Interwiring 32-34Notes Applicable to the Standard Interwiring 35-363 Connector Inse

26、rt Layout 37-394 MLS Label Attributes 40-47Notes Applicable to MLS Label Attributes 485 MLS ARINC 429 Label Attributes 496 Typical Audio Output Test Procedures 507 Environmental Test Categories 518 MLS Channel Pairing 52-599 Antenna Design 60-6210 MLS/ILS Sensitivity Guideline 6311 CDU Connector Lay

27、out 64-6512 Table of MLS Warning Outputs 66Notes on Table of MLS Warning Outputs 6713 Letter from FAA Re: Potential Flammability Hazards 68-69ARINC CHARACTERISTIC 727 - Page 11.0 INTRODUCTION AND DESCRIPTION1.1 Purpose of This CharacteristicThis document sets forth the desired characteristics ofMLS

28、receiver processors intended for installation in alltypes of commercial transport aircraft. The intent of thisdocument is to provide general and specific guidance forthe development and installation of MLS receiverprocessors primarily for airline use. This characteristicwill describe the desired ope

29、ration capability of theequipment, the standards necessary to ensureinterchangeability, form factor, and pin assignments.Equipment manufacturers should note that this documentaims to encourage them to produce maintenance-free, highperformance equipment rather than that of minimumweight and dimension

30、s. They are at liberty to accomplishthis objective by means of design techniques they considerto be the most appropriate, as their airline customers areinterested primarily in the end result rather than the meansemployed to achieve it.1.2 Function of the EquipmentThe function of the airborne MLS rec

31、eiver processor isthe reception and processing of the MLS azimuth signals,the elevation signals, and the data transmitted from theMLS ground stations. The airborne MLS receiverprocessor should present this information to a pilotsvisual display, to an Automatic Flight Control System andother on-board

32、 systems in a form acceptable for standardusage. Other documents may refer to the MLS receiverprocessor as an “Angle receiver processor”.1.3 Unit Description1.3.1 MLS Receiver Processor UnitThe MLS receiver processor unit should house all of thecomponents, electronic circuitry, etc., incident of the

33、functioning of the system, including channel selection, thereception of RF energy and the recovery of theinformation contained in the received signals. This unitshould also originate the outputs which are used (i) todrive cockpit displays, and (ii) as inputs to automaticflight control systems.1.3.2

34、Frequency ControlThen MLS receiver processor should be capable ofaccepting frequency control from a dedicated control unitor alternatively, accepting an equivalent data input from acentralized radio management system. The MLS receiverprocessor should also accept control glide path andazimuth selecti

35、on inputs. Selection inputs should utilizethe 2-wire serial digital frequency/function selectioncommand format defined in ARINC Specification 429.1.3.3 AntennasDue to various signal blockage problems, three antennasmay be needed for some installations. The MLS receiverprocessor should provide for th

36、e connection off:(i) A forward landing antenna that is not blocked on anapproach and provides reception of the MLS signals whenthe aircraft has a component of its velocity toward theground station. This antenna should be located to meetregulatory agency wheel height over thresholdrequirements.1.3.3

37、Antennas (contd)(ii) A tail antenna that is not blocked by the aircraftstructure and provides reception when the aircraft has acomponent of its velocity away from the runway served bythe ground station.(iii) An auxiliary antenna that can be mounted in alocation to complement the landing antenna. Thi

38、s antennawould aid in providing signal coverage in roll and pitch aswell as through 360 degrees of azimuth.COMMENTARYIn installations where long cable runs are used,remote amplifiers may also be necessary to obtain ausable signal amplitude. The use of remoteamplifiers is considered undesirable by th

39、e airlines.Their use should be avoided if possible.1.3.4 InstrumentationThe receiver processor output information to be displayedto the pilot should be fed to panel-mounted combinationinstruments such as C.D.Is and H.S.I.s. ThisCharacteristic provides the precise definition of thedesired receiver pr

40、ocessor / instrumentation interface.1.4 Interchangeability1.4.1 GeneralOne of the primary functions of an ARINC EquipmentCharacteristic is to designate, in addition to certainperformance parameters, the interchangeability desired foraircraft equipment produced by various manufacturers.Manufacturers

41、are referred to Section 1.6 of ARINCReport 414 for the airline industrys definitions of Termsand General Requirements for interchangeability. Asexplained in that Report, the degree of interchangeabilityconsidered necessary and attainable for each particularequipment is specified in the pertinent ARI

42、NC EquipmentCharacteristic.1.4.2 Interchangeability Desired for the ARINC 727MLS ComponentsUnit interchangeability is desired for the receiverprocessor unit regardless of the manufacturing source.Interchangeability is desired for the MLS antenna,regardless of equipment manufacturer. For installation

43、s inwhich a preamplifier is used, it is expected that thecombinations of antenna and preamplifier, which may betreated as a single unit for interchangeability purposes,will be interchangeable, regardless of equipmentmanufacturer. In recognition of the widely varyingcontrol unit designs used in the p

44、ast and expected in thefuture, unit interchangeability is not sought for the controlunit. Control units should, however, conform to theelectrical interface and digital signal standards set forth inthis Characteristic.1.4.3 “Generation Interchangeability”ConsiderationsThis Characteristic defines a si

45、ngle MLS receiverprocessor to function in two configurations: “retrofit” and“new generation”. It is desired that a unit may beinterchangeable between both operational installations.ARINC CHARACTERISTIC 727 - Page 21.0 INTRODUCTION AND DESCRIPTION (contd)1.4.3 “Generation Interchangeability” Consider

46、ations (contd)In order to achieve full benefit offered by theserecommendations the industry desires to maximizebackward compatibility with earlier landing systems.Provisions to ensure forward-looking “generationinterchangeability” (as best can be predicted) are includedin this document to guide manu

47、facturers in futuredevelopments.1.5 Regulatory ApprovalThe equipment described in this document should meet allapplicable FAA regulatory requirements. This ARINCCharacteristic does not and cannot set forth the specificrequirements that an equipment must meet to be assuredof FAA approval. This inform

48、ation must be obtainedfrom the FAA itself.ARINC CHARACTERISTIC 727 - Page 32.0 INTERCHANGEABILITY STANDARDS2.1 IntroductionThis Section of this Characteristic sets forth the specificform factor, mounting provisions, interwiring, input andoutput interfaces and power supply characteristics desiredfor

49、these MLS receiver processors.Manufacturers should note that although thisCharacteristic does not preclude the use of different formfactors and interwiring features, the practical problem ofredesigning what will then be a standard aircraftinstallation to accommodate some special system couldvery well make the use of that other design prohibitivelyexpensive for the customer. They should recognize,therefore, the practical advantages of developingequipment in accordance with the standards set forth inthis document.2.2 Form Factors, Connectors & Index PinCoding2.2.1 MLS Receiver P