ARINC 735-2-1993 Traffic Alert and Collision Avoidance System (TCAS)《交通警报和防止空中相撞系统1988包括附录1和2》.pdf

《ARINC 735-2-1993 Traffic Alert and Collision Avoidance System (TCAS)《交通警报和防止空中相撞系统1988包括附录1和2》.pdf》由会员分享，可在线阅读，更多相关《ARINC 735-2-1993 Traffic Alert and Collision Avoidance System (TCAS)《交通警报和防止空中相撞系统1988包括附录1和2》.pdf（151页珍藏版）》请在麦多课文档分享上搜索。

1、 TRAFFIC ALERT AND COLLISIONAVOIDANCE SYSTEM (TCAS)ARINC CHARACTERISTIC 735-2PUBLISHED: JANUARY 15, 1993AN DOCUMENTPrepared byAIRLINES ELECTRONIC ENGINEERING COMMITTEEPublished byAERONAUTICAL RADIO, INC.2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401Copyright 1993 byAERONAUTICAL RADIO, INC.2551 Riva RoadA

2、nnapolis, Maryland 21401-7465 USASupplement 2 will not be made availableseparately due to the extensive changes toprevious version of the standard. It isincluded in its entirety in Characteristic735-2.ARINC CHARACTERISTIC 735-2TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS)Published: January 15,

3、 1993Prepared by the Airlines Electronic Engineering CommitteeCharacteristic 735 Adopted by the Airlines Electronic Engineering Committee: October 19, 1988Characteristic 735-1 Adopted by the Airlines Electronic Engineering Committee: October 26, 1989Characteristic 735-2 Adopted by the Airlines Elect

4、ronic Engineering Committee: November 5, 1992FOREWORDActivities of AERONAUTICAL RADIO, INC. (ARINC)and thePurpose of ARINC CharacteristicsAeronautical Radio, Inc. is a corporation in which the United States scheduled airlines arethe principal stockholders. Other stockholders include a variety of oth

5、er air transport companies,aircraft manufacturers and non-U.S. airlines.Activities of ARINC include the operation of an extensive system of domestic andoverseas aeronautical land radio stations, the fulfillment of systems requirements to accomplishground and airborne compatibility, the allocation an

6、d assignment of frequencies to meet thoseneeds, the coordination incident to standard airborne communications and electronics systems andthe exchange of technical information. ARINC sponsors the Airlines Electronic EngineeringCommittee (AEEC), composed of airline technical personnel. The AEEC formul

7、ates standardsfor electronic equipment and systems for the airlines. The establishment of EquipmentCharacteristics is a principal function of this Committee.An ARINC Equipment Characteristic is finalized after investigation and coordination withthe airlines who have a requirement or anticipate a req

8、uirement, with other aircraft operators,with the Military services having similar requirements, and with the equipment manufacturers.It is released as an ARINC Equipment Characteristic only when the interested airline companiesare in general agreement. Such a release does not commit any airline or A

9、RINC to purchaseequipment so described nor does it establish or indicate recognition of the existence of anoperational requirement for such equipment, not does it constitute endorsement of anymanufacturers product designed or built to meet the Characteristic. An ARINC Characteristichas a twofold pur

10、pose, which is:(1) To indicate to the prospective manufacturers of airline electronic equipment theconsidered opinion of the airline technical people, coordinated on an industrybasis, concerning requisites of new equipment, and(2) To channel new equipment designs in a direction which can result in t

11、hemaximum possible standardization of those physical and electrical characteristicswhich influence interchangeability of equipment without seriously hamperingengineering initiative.iiARINC CHARACTERISTIC 735TABLE OF CONTENTSITEM SUBJECT PAGE1.0 INTRODUCTION AND DESCRIPTION 11.1 Purpose of this Docum

12、ent 11.2 System Description 11.3 TCAS 11.4 Unit Description 11.4.1 TCAS Computer Unit 11.4.1.1 TCAS Computer Unit 11.4.2 Control Unit 11.4.3 TCAS Display 11.4.4 Antennas 11.5 Altitude Reporting Data 11.6 Interchangeability 21.6.1 General 21.6.2 Interchangeability Desired for the ARINC 735 TCAS 21.6.

13、3 “Generation Interchangeability“ Considerations 21.7 Regulatory Approval 22.0 INTERCHANGEABILITY STANDARDS 32.1 Introduction 32.2 Form Factor, Connectors and Index Pin Coding 32.2.1 TCAS Computer Unit 32.2.2 Antenna 32.2.3 Relationship of ARINC 735 to ARINC 718 32.3 Interwiring 32.4 Power Circuitry

14、 32.4.1 Primary Power Input 32.4.1.1 AC Power Input 42.4.1.2 DC Power Input 42.4.2 Power Control Circuitry 42.4.3 The Common Ground 42.4.4 The AC Common Cold 42.5 Environmental Conditions 42.6 Cooling 42.7 Grounding and Bonding 42.8 Standardized Signaling 42.8.1 ARINC 429 DITS Data Bus 42.8.2 Standa

15、rd “Open“ 52.8.3 Standard “Ground“ 52.8.4 Standard “Applied Voltage“ Output 52.8.5 Standard Discrete Input 52.8.6 Standard Discrete Output 52.8.7 Standard Program Pin Input 63.0 TCAS FUNCTIONAL DESCRIPTION 73.1 Aural Advisory and Visual Annunciator Outputs 73.1.1 Aural-Advisory Signals 73.1.2 Synthe

16、sized Voice Output 73.2 Aircraft Interfaces 73.2.1 Radio Altimeter/Barometric Altimeter 73.2.2 Aircraft Climb Performance Inputs 73.2.3 Reserved Flight/Performance Management Interface 73.3 Interface with Mode S Transponder 83.4 TCAS Displays 83.4.1 Resolution Advisory (RA) Display 83.4.2 Traffic Ad

17、visory Display 83.4.3 Normal and Failure Mode Annunciations 83.4.3.1 RA/VSI Displays 83.4.3.2 Traffic and TA/RA/VSI Displays 93.4.4 Display Status Discrete 93.5 Discrete Signals 93.5.1 Discrete Input Signals 93.5.1.1 Climb Inhibit Discrete Input 103.5.1.2 Increased Climb Inhibit Discrete Input 10iii

18、ARINC CHARACTERISTIC 735TABLE OF CONTENTSITEM SUBJECT PAGE3.5.1.3 Aircraft Performance Limit Program Discrete Input 103.5.1.4 Landing Gear Discrete Input 103.5.1.5 Air/Ground Discrete Input 103.5.1.6 Ground Display Mode Discrete Input 103.5.1.7 Display All Traffic Discrete Input 103.5.1.8 Advisory I

19、nhibit Discrete Input 103.5.1.9 Advisory/Annunciator Cancel 113.5.1.10 RA/TA System Status Discrete Inputs 113.5.2 Discrete Output Signals 113.5.2.1 Resolution Advisory Discrete Input 113.5.2.2 TA Display Enable Discrete Output 113.5.2.3 TA Aural Advisory Discrete Output 113.5.2.4 Visual Annunciator

20、 Discrete Output 113.5.2.5 TCAS System Status Discrete Output 113.5.2.5.1 Standby Mode Selected 113.5.2.5.2 TA Only Mode Selected 123.5.2.5.3 TA/RA Mode Selected 123.5.2.6 Software Part Number Discrete Output 123.6 Program Pins 123.6.1 Aircraft Performance Altitude Limit 123.6.2 Cable Delay 123.6.3

21、Audio Tone Enable Program 123.6.4 Ground Display Mode Program 123.6.5 TA Display Intruder Limit 123.6.6 Display All Traffic/Threat Traffic 123.6.7 Audio Output Level 123.7 Test Pins 134.0 FUNCTIONAL TEST, MONITORING AND BUILT-IN TEST 14EQUIPMENT (BITE)4.1 TCAS Functional Test 144.2 Indicator Respons

22、e 144.2.1 Extended Test Text Display 154.3 Integrity Monitor Display 154.4 Built-in Test Equipment (BITE) 154.5 BITE Display 164.6 Fault Monitor 164.7 BITE Initiation 164.8 Monitor Memory Output 164.9 Provisions for Automatic Test Equipment 164.9.1 General 164.9.2 Unit Identification 174.9.2.1 Pin A

23、llocation 174.9.3 Use of ATLAS Language 175.0 ANTENNAS 185.1 Omnidirectional Antenna 185.1.1 Impedance and VSWR 185.1.2 Gain and Polarization 185.1.3 Power Rating 185.1.4 Radiation Pattern 185.1.5 Connector 185.1.6 Continuity Check 185.2 Directional Antenna 185.3 Environmental Considerations 185.4 L

24、-band Systems Physical Isolation 185.5 Antenna Installation 195.6 Antenna and Cable Characteristics 195.6.1 Total Interconnection Losses 195.6.2 Differential Cable Losses 195.6.3 Differential Phase Delay 195.7 Anti-Icing 19ivARINC CHARACTERISTIC 735TABLE OF CONTENTSITEM SUBJECT PAGE6.0 VSI/TCAS DISP

25、LAY 206.1 Standard VSI/TCAS Display 206.1.1 Physical Description 206.1.2 115 VAC Power Input 206.1.3 Display Presentation 206.1.4 Input Data Bus 216.1.5 Display Status Output 216.1.6 Lamp Test/Display Discrete Input 216.2 Alternative TCAS Display Indicators 216.3 Integral Lighting 216.4 Environmenta

26、l Conditions 217.0 SIMULATOR INSTALLATION 227.1 Use in Simulators 22ATTACHMENTS1A TCAS Mode S Architecture 231B TCAS/Dual Mode Intra System Data Link Diagram 241C TCAS Display and Annunciation Interface Diagram 25-261D TCAS/Dual Mode S Power Input Configuration Diagram 271E TCAS Input Signal Diagram

27、 281F TCAS Output Signal Diagram 291G TCAS Program Pin Signal Diagram 302 TCAS Computer Unit Connector Positioning 313A Standard Interwiring 32-373B Notes Applicable to the Standard Interwiring 38-424 TCAS Computer Unit Connector Insert Layout 43-455A Mode A Reply Code Combinations 465B ATCRBS Reply

28、 Code Pulse Characteristics 476A ARINC 429 Data Bus Interface Definition 48-536B Coordination Data Bus Definition 546C Dits Control Word for TCAS (and Mode S Transponder) 556D Dits Control Word for TCAS, Mode S Transponder and TA/RA Displays 566E TCAS Vertical RA Data Output Word 57-586F Reserved fo

29、r TCAS Horizontal RA Data Output Word 596G TCAS Traffic Advisory, Intruder Range Word 606H TCAS Traffic Advisory, Intruder Altitude Word 616J TCAS Traffic Advisory, Intruder Bearing Estimate Word 626K Standard ARINC 429 Format for Bus 1 Word 2 - Transponder to TCAS 636L Standard ARINC 429 Format for

30、 Bus 1 Word 8 - Transponder to TCAS 646M Standard ARINC 429 Format for Bus 1 Word 3 - Transponder to TCAS 656N Standard ARINC 429 Format for Bus 1 Word 4 - Transponder to TCAS 666P Standard ARINC 429 Format for Bus 1 Word 5 - Transponder to TCAS 676Q Standard ARINC 429 Format for Bus 1 Word 6 - Tran

31、sponder to TCAS 686R Standard ARINC 429 Format for Bus 1 Word 7 - Transponder to TCAS 696S Standard ARINC 429 Format for Bus 1 Word 1 - TCAS to Transponder 706T Standard ARINC 429 Format for Bus 2 Word 1 - TCAS to Transponder 716U Standard ARINC 429 Format for Bus 2 Word 2 - TCAS to Transponder 726V

32、 Standard ARINC 429 Format for Bus 2 Word 3 - TCAS to Transponder 736W Standard ARINC 429 Format - FMS to TCAS 746X Altitude Select Limits Word 756Y TCAS Fault Summary Word 766Z-1 TCAS Display Start of Transmission (STX) Record Word 776Z-2 TCAS Display Text Display Data Control Word 786Z-3 TCAS Disp

33、lay Text Display Data Character Word 796Z-4 TCAS Display End of Transmission (EOT) Word 807A Input/Output Circuit Standards 817B ARINC 429 Transmitter Logic States 828 Suppression Pulse System Characteristics 83-849A Typical Blade Antenna 859B Bearing Antenna Mounting Layout 869C TCAS Directional An

34、tenna Envelope 87vARINC CHARACTERISTIC 735TABLE OF CONTENTSITEM SUBJECT PAGEATTACHMENTS9D Aircraft Installations 8810 TCAS Antenna Configuration 8911 Figure Deleted 9012 ARINC High Speed Bus (100 KHZ Protocol) for TCAS-Transponder 91-95Interface13 Environmental Test Categories 96-9714-1 Standard VSI

35、/TCAS Display Interwiring 9814-2 Notes to Standard RA Display Interwiring 9914-3 Standard VSI/TCAS Display Connector Layout 10015-1 Alternate #1 VSI/TCAS Display Interwiring 10115-2 Notes to Alternate #1 VSI/TCAS Display Interwiring 102-10315-3 Alternate VSI/TCAS Connector Layout 10416-1 Alternate #

36、2 VSI/TCAS Display Interwiring 10516-2 Notes to Alternate #2 VSI/TCAS Display Interwiring 10616-3 RA Only VSI/TCAS Connector Layout 10717-1 Alternate #3 VSI/TCAS Display Interwiring 10817-2 Notes to Standard RA Display Interwiring 109-11017-3 Alternate #3 VSI/TCAS Connector Layout 11118 TCAS System

37、Functional Test Normal Output Definition 112APPENDICES1 ATA Recommended Standards for TCAS II Display, Symbology 113-135and Controls2 Label 270, Resolution Advisory Word, Reporting Combinations 136-137viARINC CHARACTERISTIC 735 - Page 11.0 INTRODUCTION AND DESCRIPTION1.1 Purpose of this DocumentThis

38、 document describes a Traffic Alert and CollisionAvoidance System (TCAS) specifically designed forinstallation in commercial type aircraft. When interfacedwith a Mode S radar beacon transponder in the mannerdescribed in this document and supplemented withappropriate displays and control panel, the t

39、wo unitsfunction as an Airborne Separation Assurance SystemCOMMENTARYTCAS has evolved as a system. Each version hasbeen given a title. The first version, TCAS I, isintended for general aviation. The second version,intended for air transport use, was designated TCASII. The third version, whose functi

40、onal definitionwas in progress at the time of the development ofthis Characteristic, was termed TCAS III.This Characteristic is not intended to address TCASIII equipment or capability. Some accommodationhas been made, in hopes that these provisions willfacilitate the incorporation of TCAS III capabi

41、lities ata later date.1.2 System DescriptionManufacturers and users should be aware that TCAS isdescribed in depth in two other documents. The U.S.National Aviation Standard on TCAS, FAA documentnumber 6367.1, describes the “signal-in-space“ standard.The RTCA Document DO-185, “Minimum OperationalPer

42、formance Standards for TCAS“ provides an essentiallycomplete technical description of the system. The systemcapability desired by the airlines is described as“minimum TCAS II“ in RTCA DO-185. Readers of thisARINC document should check with the FAA and RTCAconcerning the status of the referenced docu

43、ments beforemaking use of them.1.3 TCASThe function of TCAS is to determine the range, altitudeand bearing of other aircraft equipped with ModeS/ATCRBS transponders with respect to the location ofown aircraft. The system monitors the trajectory of theseaircraft for the purpose of determining if any

44、of themconstitute a potential collision hazard. The system isresponsible for estimating the separation at closestapproach and determining if a potential conflict exists. Ifso, the system should display an advisory to the pilot. Incases defined in this document, the system should alsoprovide guidance

45、 for the optimum vertical avoidancemaneuver. The correctness of the avoidance maneuver isensured by coordination of mutual intentions with theother TCAS equipped aircraft through the Mode Stransponder.1.4 Unit Description1.4.1 TCAS Computer UnitThe TCAS Computer Unit should house all of thecomponent

46、s incident to the functioning of the TCASsystem other than those necessary to effect the display ofcollision avoidance and traffic advisories to the aircrew,for flight crew control of system operation, and electronicsnecessary at the antenna.1.4.1.1 TCAS Computer Unit Sensitivity LevelTCAS sensitivi

47、ty level selection will have three modes:Automatic, Standby and TA Only. In the Automaticmode, sensitivity level selection will be made by thecomputer unit in accordance with inputs from the radioaltimeter and the barometric altimeter. When theAutomatic mode is selected, both traffic advisories (TA)

48、and resolution advisories (RA) are generated whenappropriate. In the Standby mode, TCAS RFinterrogations are inhibited and TCAS cannot generateTAs or RAs.1.4.2 Control UnitAny needed manual control for the TCAS unit should beprovided on the control panel of its associated Mode STransponder unit. As

49、there is no direct link between thiscontrol panel and the TCAS unit, control information willbe delivered to the TCAS via the transponder. Thecontrol panel should provide the needed interface to theMode S transponder required for the TCAS system.Communications links from the Mode S transponder unitto the TCAS should be the two-wire serial digital systemdescribed in ARINC Specification 429, “Mark 33 DigitalInformation Transfer System (DITS)“. Details of theMode S Transponder control panel are contained inARINC Characteristic 718, “Mark 3 Air Traffic ControlTransponder (ATCRBS/MODE S).1.4