ARINC 708-6-1991 Airborne Weather Radar《空中传播雷达1978包括附录1到6》.pdf

《ARINC 708-6-1991 Airborne Weather Radar《空中传播雷达1978包括附录1到6》.pdf》由会员分享，可在线阅读，更多相关《ARINC 708-6-1991 Airborne Weather Radar《空中传播雷达1978包括附录1到6》.pdf（115页珍藏版）》请在麦多课文档分享上搜索。

1、 AIRBORNE WEATHER RADARARINC CHARACTERISTIC 708-6PUBLISHED: NOVEMBER 15, 1991AN DOCUMENTPrepared byAIRLINES ELECTRONIC ENGINEERING COMMITTEEPublished byAERONAUTICAL RADIO, INC.2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401This document is based on material submitted by variousparticipants during the draf

2、ting 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 documen

3、t shall constitute an acceptancethereof “as is” and be subject to this disclaimer.FOREWORDActivities of AERONAUTICAL RADIO, INC. (ARINC)and thePurpose of ARINC CharacteristicsAeronautical Radio, Inc. is a corporation in which the United States scheduled airlines are the principalstockholders. Other

4、stockholders include a variety of other air transport companies, aircraft manufacturers and non U.S.flag airlines.Activities of ARINC include the operation of an extensive system of domestic and overseas aeronautical landradio stations, the fulfillment of systems requirements to accomplish ground an

5、d 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 EngineeringCommittee (AEEC), composed of a

6、irline 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.An ARINC Equipment Characteristic is finalized after investigation and coordination with the airlin

7、es whohave a requirement or anticipate a requirement, with other aircraft operators, with the Military services having similarrequirements, and with the equipment manufacturers. It is released as an ARINC Equipment Characteristic only whenthe interested airline companies are in general agreement. Su

8、ch a release does not commit any airline or ARINC topurchase equipment so described nor does it establish or indicate recognition of the existence of an operationalrequirement for such equipment, not does it constitute endorsement of any manufacturers product designed or built tomeet the Characteris

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

10、t designs in a direction which can result in the maximum possiblestandardization of those physical and electrical characteristics which influence interchangeability ofequipment without seriously hampering engineering initiative.iiREPLACEMENT PAGE REVISED: November 15, 1991Copyright 1992 byAERONAUTIC

11、AL RADIO, INC.2551 Riva RoadAnnapolis, Maryland 21401ARINC CHARACTERISTIC 708-6 AIRBORNE WEATHER RADARPublished: November 15, 1991Prepared by the Airlines Electronic Engineering CommitteeCharacteristic 708 Adopted by the Airlines Electronic Engineering Committee: May 4, 1978Characteristic 708 Adopte

12、d by Industry: August 15, 1979Characteristic 708-1 Adopted by the Airlines Electronic Engineering Committee: August 30, 1979Characteristic 708-2 Adopt ed by the Airlines Electronic Engineering Committee: June 13, 1989Characteristic 708-3 Adopted by the Airlines Electronic Engineering Committee: Dece

13、mber 10, 1981Characteristic 708-4 Adopted by the Airlines Electronic Engineering Committee: November 4, 1982Characteristic 708-5 Adopted by the Airlines Electronic Engineering Committee: October 13, 1983Characteristic 708-6 Adopted by the Airlines Electronic Engineering Committee: August 19, 1986REP

14、LACEMENT PAGE REVISED: November 15, 1991ARINC CHARACTERISTIC 708-6TABLE OF CONTENTSITEM SUBJECT PAGEiii1.0 INTRODUCTION AND DESCRIPTION 11.1 Purpose of this Equipment 11.2 Purpose and Limitations of this Characteristic 11.3 System Description 11.3.1 System Architecture 11.3.2 System Configuration 11

15、.3.3 Unit Description 11.3.3.1 Transmitter-Receiver 11.3.3.2 Antenna 11.3.3.3 Control/Display Unit 21.3.3.4 Display Unit 21.3.3.5 Control Panel 21.4 Interchangeability 21.4.1 General Requirements for Interchangeability 21.4.2 “Generation Interchangeability” Considerations 21.4.3 Interchangeability R

16、equirements for ARINC 708 Equipment 21.5 Regulatory Approval 21.6 Reliability 22.0 INTERCHANGEABILITY STANDARDS 32.1 Form Factors, Connectors and Index Pin Coding 32.1.1 Transmitter-Receiver (T-R) 32.2 Mounting Trays for T-R Units 32.3 Antenna Unit Form Factor and Connectors 32.4 Display Unit Form a

17、nd Connector 32.5 Control Unit 32.6 Interwiring 32.7 Power Circuitry 32.7.1 Primary AC Power Input 32.7.2 Power Control Circuitry 32.8 Weights 42.9 Environmental Conditions 42.10 Stabilization Signal Characteristics 42.11 Stabilization Signal Loading 42.12 Radome 42.13 RF Transmission Line 42.13.1 X

18、-Band 42.13.2 C-Band 42.14 Cooling-General 42.14.1 T-R Unit 52.14.2 Display and CDC Cooling 52.15 Antenna Mount 52.15.1 Standard Attachment Hole Pattern 52.15.2 Mounting Adjustments 52.16 Antenna Gain Compensation 52.17 Environmental Conditions 52.18 Grounding and Bonding 52.19 Transmission Line Pre

19、ssure 52.20 System Configuration Programming Pins 52.21 Display Data Bus Termination 63.0 SYSTEM DESIGN AND PERFORMANCE REQUIREMENTS 73.1 Range Performance, Weather 73.2 Performance Index 73.3 Range Performance, Ground Mapping 83.4 Range Displays 83.4.1 Range Select/Display Erase 93.5 Display Sector

20、 (Scan Angle) 93.5.1 Normal Angle 93.5.2 Reduced Sector Scan 9REPLACEMENT PAGE REVISED: November 15, 1991ARINC CHARACTERISTIC 708-6TABLE OF CONTENTSITEM SUBJECT PAGEiv3.6 Display Visibility 93.7 Iso-Echo-Contour 93.8 Radio Frequency 93.8.1 X-Band System 93.8.2 C-Band System 93.9 Self-Test 93.10 Oper

21、ating Conditions 103.11 Accuracy of Display 103.12 Dual Operation 103.13 Sensitivity Time Control (STC) 103.14 Turbulence Detection 103.15 Color Displays 103.16 Control Hierarchy 113.16.1 Dedicated Radar Displays 113.17 Antenna Tilt Control 113.17.1 Manual Tilt Control 113.17.2 Automatic Tilt Contro

22、l 113.18 Anti-Clutter 113.19 Automatic Weather/Turbulence Alert 113.20 Control Data Bus 113.21 Display Data Bus 113.22 LRU Failure Indicator 123.23 Auxiliary Data Bus 123.24 Master/Slave Operations 123.25 ON/OFF Control 124.0 TRANSMITTER-RECEIVER UNIT DESIGN 134.1 General 134.2 Automatic Gain Contro

23、l (AGC) 134.3 STC 134.4 Automatic Frequency Control (AFC) 134.5 Range Resolution 134.6 Receiver Dynamic Range 134.7 Antenna Stabilization 134.8 Serial Digital Control Input 134.9 Serial Digital Data Output 134.10 Test Facilities 134.10.1 Manual Self-Test 144.10.2 Auto Test (optional) 144.10.3 Flight

24、 Line Maintenance BITE 144.11 Service Adjustments 144.12 Time Counter 144.13 Cooling 144.14 Magnetic Field 144.15 Waveguide Window 145.0 ANTENNA UNIT DESIGN 155.1 Design Criteria 155.2 Scan Angle and Rate 155.2.1 Sector Scan 155.2.2 Scan Rate 155.3 Tilt 155.4 Stabilization 155.4.1 System Accuracy 15

25、5.4.2 Improved Line-of-Sight Antenna 165.4.3 Independent Roll Stabilization 165.4.4 Stabilization Limit Annunciation 165.5 Beam Width and Shape 165.6 Mounting 165.7 Antenna Gain Compensation 16REPLACEMENT PAGE REVISED: November 15, 1991ARINC CHARACTERISTIC 708-6TABLE OF CONTENTSITEM SUBJECT PAGEv6.0

26、 CONTROL DISPLAY UNIT (CDU) 176.1 General Design Criteria 176.2 Controls 176.2.1 Display Controls (Typical) 176.2.2 System Controls (Typical) 176.3 Screen 176.4 Focusing 176.5 Resolution 176.6 Panel Lighting 176.7 Deflection System 176.8 Shielding 176.9 Control Data Bus 186.10 Display Data Bus 186.1

27、1 Auxiliary Data Bus 186.12 System Performance Annunciator 186.13 Cooling 186.14 Auxiliary Data Display 186.14.1 Character Font 186.14.2 Display Size 186.14.3 Modes of Operation 186.14.4 Special Use of Characters 186.15 Caution and Mode Indicators 187.0 SEPARATE DISPLAY UNIT (DU) DESIGN 197.1 Genera

28、l 197.2 Controls 197.3 Display Data Bus 197.4 Cooling 197.5 Auxiliary Data Bus 198.0 CONTROL PANEL DESIGN 208.1 General 208.2 Controls 208.3 Control Data Bus 209.0 RADOME DESIGN 219.1 General 219.2 Transmissivity 219.3 Incident Reflection 219.4 Sidelobe Levels 219.5 Anti-Icing 229.6 Bore Sight Error

29、s 2210.0 PROVISIONS FOR AUTOMATIC TEST EQUIPMENT 22a10.1 General 22a10.2 Unit Identification 22a10.2.1 Pin Allocation 22a10.3 Use of ATLAS Language 22a11.0 BUILT-IN TEST EQUIPMENT (BITE) 2311.1 Built-In Test Equipment (BITE) 2311.2 BITE Display 2311.3 Fault Monitor 2311.4 Self-Test Initiation 2411.4

30、.1 Self-Test Initiation 2411.4.2 Automatic Self-Test Operation 2411.4.3 Manual Self-Test Operation 2411.5 Monitor Memory 2411.6 Monitor Memory Output 24REPLACEMENT PAGE REVISED: November 15, 1991ARINC CHARACTERISTIC 708-6TABLE OF CONTENTSITEM SUBJECT PAGEviATTACHMENTS1 Notes Applicable to Standard I

31、nterwiring 25-262-1 Single System Standard Interwiring (Single or Dual Displays) 27-292-2 Dual System Standard Interwiring (Single or Dual Displays) 30-323 Transmitter/Receiver Connector Layout 33-344-1 Transmitter/Receiver Form Factor (X-Band) 354-2 Transmitter/Receiver Form Factor (C-Band) 374-3 W

32、aveguide Connection X-Band Outline 384-4 Waveguide Connection T-R Unit (X-Band) 394-5 Waveguide Connection Rack Unit (X-Band) 404-6 Dual Installation (X-Band) 415 Control/Display and Display Connector Layout 426-1 Display Form Factor 436-2 Display Mount 447-1 Control Panel Connector Layout 457-2 Con

33、trol Panel Form Factor 468-1 Standard Aircraft Mounting Provisions for Antenna 478-2 Antenna Space Provisions (Maximum Swept Volume) 488-3 Analysis of Antenna Mounting Roll Tolerances 499 Antenna Connector Layout 5010-1 Antenna Form Factor (X-Band Line of Sight) 5110-2 Antenna Form Factor (C-Band Li

34、ne of Sight) 5211-1 Installation Configurations 0, 2 and 4 (Single T/R) 5311-2 Installation Configurations 1, 2 and 5 (Single T/R-Dual Display) 5411-3 Installation Configuration 6 (Single T/R-Triple Display) 5511-4 Installation Configurations 0, 2 and 4 (Dual T/R) 5611-5 Installation Configurations

35、1, 2 and 5 (Dual T/R-Dual Display) 5711-6 Installation Configuration 6 (Dual T/R-Triple Displays) 5811-7 Control Bus Usage 5911-8 Data Bus Usage 6012 Performance Index Curves 6113 Radar Stabilization Tolerances Summary 6214 Environmental Test Categories 6315-1 Weather Radar Serial Control Data 64-65

36、15-2 Weather Radar Display Data Bus Format 66-7116 Installation Configuration Programming 7217 Display Data Bus Termination 73-7718 Auxiliary Data Bus Interface 7419 International Standards Organization Code #5 7820 Waveguide Switch Electrical Interface 79APPENDICES1 Physical, Electrical and Signal

37、Characteristics of Display Data Bus 80-811-1 Timing Characteristics 82-832 Chronology and Bibliography 84-853 Non-Standard Applications 86-88REPLACEMENT PAGE REVISED: March 15, 1982ARINC CHARACTERISTIC 708 - Page 11.0 INTRODUCTION AND DESCRIPTION1.1 Purpose of this EquipmentThis Characteristic descr

38、ibes highly reliable, low-cost,lightweight airborne weather radar equipment intendedfor installation in commercial transport type aircraft. Itsprimary purpose is weather detection, ranging andanalysis. Its secondary purpose is ground mapping tofacilitate navigation by display of significant landcont

39、ours. Its tertiary purpose is displaying alpha-numeric information from an external source.1.2 Purpose and Limitations to this CharacteristicThis characteristic has been prepared by the Industry totake advantage of recent, technical advances in airborneweather radar. Emphasis is placed upon weatherd

40、etection/analysis capability and performance,reliability, installation ease, digital aircraft systemcompatibility and reduced cost of ownership.COMMENTARYCurrent integrated circuit technology coupled withadvance packaging techniques should also reduceweight and volume of this system. As muchfreedom

41、as possible is given to equipmentdesigners to provide the required performance inthe most efficient manner and to meet individualairlines preferences provided standard packingand interwiring are used. Electrical characteristicof the weather radome are defined in Section 9. Itis to be understood, how

42、ever, that mechanicaldesign must remain the responsibility of theairframe manufacturer.1.3 System Description1.3.1 System ArchitectureThe system should be viewed as a weather sensorconsisting of a Transmitter-Receiver (T-R) and Antennawhich functions through a standardized electricalinterface to the

43、 control and display elements. Thedisplay may consist of a dedicated “Weather RadarIndicator” unit or it may be one of several functions on a“Multi-Function Display” (MFD). The controls may beprovided by a separate unit or integrated into the displaywhere a Control/Display Unit (CDU) is provided. Th

44、isconcept provides for the independent future upgrading ofthe sensor and/or its use with other display systems.COMMENTARYData transfer between units of the system should beprimarily serial digital. Information originatingfrom the control panel or other source should bepresented to the T-R on a seria

45、l digital bus. The T-R should accept properly addressed control inputs,respond to these inputs and relay the selections tothe indicator together with relative azimuth andrange related receiver data. The display shouldaccept the control and range data from the T-R,store the data in digital memory and

46、 display theinformation for the user.1.3.2 System ConfigurationThe standardized units described by this characteristiccan be designed into three basic aircraft installationconfigurations:a. Three Unit/Dedicated Display System Consistsof an Antenna, Transmitter-Receiver and acombined control-Display

47、Unit dedicated forthe exclusive use of the Weather Radar system.b. Three Unit/Multi-Function Display SystemConsists of an Antenna, Transmitter-Receiverand Control Unit with the display functionsprovided through a separate Multi-FunctionDisplay (MFD) system.c. Four Unit System consists of an Antenna,

48、Transmitter-Receiver, Control Unit and adedicated Display Unit.All units should be designed for an installation thatincludes single or dual transmitter-receivers, single ordual controls and/or displays and a single antenna. Blockdiagrams of typical configurations are shown inAttachment 11.The stabil

49、ization signals, control information and displaydata should be serial digital. The stabilization signalsshould conform to ARINC 704 Inertial ReferenceSystem or ARINC 705 Attitude and Heading ReferenceSystem. The control information bus should be the lowspeed type of ARINC 429, “Mark 33 Digital InformationTransfer System (DITS)”. The display data bus shouldconform to the characteristics of the very high speed busdescribed in Appendix 1 to this document.NOTE: The extracts from Draft 2 of the ARINC 453very high speed bus AS SET FORTH IN APPENDIX 1to this document are applicable to this We