ARINC 561-11BOOK-1975 air transport navagation sys

文件名称: ARINC 561-11BOOK-1975 air transport navagation system.pdf

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详细说明：ARINC429总线协议又称ARINC是美国航空电子工程委员会(Airlines Electronic Engineering Committee)于1977年7月提出的，并于同年节月发表并获得批准使用。它的全称是数字式信息传输系统DITS。协议标准规定了航空电子设备及有关系统间的数字信息传输要求。ARINC429广泛应用在先进的民航客机中，如B-737、B757、B-767，俄制军用飞机也选用了类似的技术。我们与之对应的标准是HB6096-SZ-01。ARINO5bJ-1175■0307517001?207■ ADDED: July 1, 1969 IMPROVED ORGAN工ZAT工oN OF ARINC CHARACTERISTIC 561-o (Including Supplements) Traditionally ARINC Equipment Characteristics and Reports are updated y sUpplements which simply describe the nature of the changes. Gen- erally such Supplements do not provide revised text material to replace the obsolete sections. When it has become necessary to reprint an ARINC Equipment Characteristic, the routine practice has been to arrange all of the applicable Supplements in the front of the document without further editorial work. The front location indicates the material in the Supple- ments, which are printed on buff-colored paper, takes precedence over the White Pages In ARINc, 561- the changes and new materdal introduced by the Supplements have been incorporated directly into the applicable specification section commentary and attachments which are reproduced on White Pages at We be- lieve the reader will find this new procedure an advantage, in that he will have a single bound document fully updated with complete specification material, commentary and attachments, all reproduced as new White Pages to reflect current status as of the latest issue date or printing dater The revisions to the White Pages are identified by a two-part Change Flag". The first part consists of the "A symbol, used to show that a change has been made. The second part uses a dash number which corres- ponds to the number of the Supplement in which the change is described In addition, a vertical line is used to indicate the extent of the updated text material The Supplements to ARINc 561 which have been fully integrated into the White Pages as described above are reproduced in the back of this arInc Characteristic. This location serves as a subtle reminder of the dif ferent function which a Supplement serves when located in the back of the document. In this case the Supplement is needed only for a record of what the change consisted of since the White Pages of the "new"docu- ment are complete in themselves With the revision to this Characteristic as described above, the document identification number now has a dash number added which corresponds to the number of the last Supplement integrated into this document Obviously, it may become necessary in the future to issue additional Supplements to further revise this document.. In this event the docu ment can be used with such future Supplements in the traditional manner ARINO55]1175■030770003921可■ FOREWORD Activites o￡ AERONAU理工 CAT RRADTO,工NC。( ARTNC and the Purpose of ARINC Characteristics Aeronautical Radio, Inc. is a corporation in which the United state scheduled airlines are the principal stockholders. other stockholders es include a variety of other air transport companies, aircraft manufacturers and foreign flag airlines Activities of ARINc include the operation of an extensive system of domestic and overseas aeronautical land radio stations, the fulfillment of systems requirements to accomplish ground and airborne compatibility the allocation and assignment of frequencies to meet those needs, the coordi- nation incident to standard airborne communications and electronics systems and the exchange of technical information. ARINC sponsors the Airlines Electronic Engineering Committee (AEE C), composed of airline technical personnel. The AEEC formulates standards for electronic equipment and systems for the airlines. The establishment of Equipment Characteristics is a principal function of this committee An ARTNC Equipment Characteris七is至 malized a￡ ter investigation and coordination with the airlines who have a requirement or anticipate a requirement, 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 companies are in general agreement. Such a release does not commit any airline or ARINC to purchase equipment so described nor does it establish or indicate recognition of the existence of an operational requirement for such equipment, nor does it constitute endorsement of any manufacturer's product designed or built to meet the characteristic. An ARINC Characteristic has a twofold purpose, which is: (1) To indicate to the prospective manufacturers of airline electronic equipment the considered opinion of the airline technical people, coordinated on an industry basis, concerning requisites o￡ new equipment, and (2)To channel new equipment designs in a direction which can result in the maximum possible standardization of those physical and electrical characteristics which influence interchangeability of equipment without seriously hampering engineering initiative ■日30717000]20國 TABLE OF CONTENES F. REVISED: June 30, 1972 ARINC CHARACTERISTIC NO, 561-8 SECTION SUBJECT GE N INLRODUCTION AND DESCRIPTION 1。1 Purpose Functions and Modea of Operation BaB⊥ c Modes of Operation 12.2 Specific Functiona and outputs Re1⊥ab1111 1.4 Unit Description 1。4。1 av土 gation Unit 4:2 pee*rontesIa4+-pttenal+ Delete 113333333 王,4.3 Control/Display (C/D)Unit 1。4。4 Mode Selector Panel 1。4。5 Remote Control Panel (Optional) 1。4。6 Remote Diaplay Unit (Optional) Interchangeability 1.6 Regulatory Approva STANDARDS REQUIRED TO EFFECT INTERCHANGEABILITY 7-23 Form Factors, Connectors, and Index Pin Coding Nav⊥ gation Ua1t 2.1。2 出a 8 Contro/D主 splay Un且t 2。1。4 Mode Selector Panel Remote Control Panel (Optional) 9 2。1.6 Remote Display Unit (Optional) 2。1.7 Battery Unit 9 Input and Output signal Characterisitcs 9 Standard Interring 11 Power Circuit 2,4.1 AC Power Input 11 2。41。1 Primaty Power 11 2。4。1。2 eater卫。wex 2.4。2 26vo】 t Ac Synchro Excitation、 11 2。4。3 Battery Supply 13 2,44 Battery Charger 13 2。4。5 Airplane Computer BuB 13 2.4.5.1 Standby Computer Bu 13 24.5。2 Optional Full-Time Computer Bus 13 2,46 Power Control Circuitry 13 2。5 Weight 15 2.6 Environment阻1cond七L。nB 17 2.7 Navigat⊥ on Unit Mounting 19 2.7.1 Navigation Unit Orientation 19 2。7。2 Navigation Unit Mounting Tolerances 19 2.8 External Program Control 2.8。1 External Program ControlCommon 2.8.2 NAV Un,t orientation 21 Subsonic and sst Functions 21 TAS Selection of Input 21B 2。 Steering Signa 2.9 INS Inter-Communications 2。10 Inter-System Comparison 23 2。11 Control /Diaplay Operational Characteristic 23 Switching Logic, General 23 2。112 Mode Selection Logic 23B SYSTEM DESIGN CONSIDERATIONS 25 3.1 25 3。1.1 Basic or Minimum Inertial Navigator 25 3.1.2 Relationship to the ARINc 562 Computer 25 3L.3 Relationship to the Future Compast 25 3。1,4 Relationship to Doppler Radar 27 3.1.5 World-WHde Self-Contained Navigation 27 3.1,6 crew如 uat Be如 ble to read-0 ut Any工 aput Instruct,ong 27 3:1.7 Attitude Output Iaolation 27 3.1.8 Navigation Way-points 27 3。19 Navigation Leg Switching 3。110 Navgatyon Leg Switching Alert Light 31 3.L。11 Syetem Performance at Zero Velocity 3.1。12 Possible Use of Inertial Signals With Autopilot Approach Couple Basic Mod f System Operatic of￡(oF) 3。2.2 Standby. (STDY) 33 Normal Alignment (NORM ALIGN) 33 Reference Alignment (REF ALIGN)-+ Optional 35 Test (TEST) 35 4。2。6 Attitude (ATT) 35 五5 PROBLEM HARD COPY REPLACEMENT PAGE TABLE OF CONTENTS (Cont'd) 3075l?0013己■ ARTNC CHARACTERTSTIC 561-11 REVISED: April 30, 1974 SECTION SUBJECT PAGE 3.3 System Contro1 37 trol 37 3.3.2 Loading control 3。3。21 Push Button Loading 37 3。3.2.2。 Automatic Load且ng 37 Semi-Automatic loadiny 3。3.3 37 37 System Inputs 3.4.1 Altitude Airspeed 3。4.3 3。4,4 Da -11 Automatic Initialization (Cu 3 3.4.5 Warning工 nputs 39 3。4。5。1 ADS True Airspeed Warning 39 3.4.5,2 Digital Data Input Warning 41 Outputs 41 3.5。1 Analog Outputs 41 3。5.2 Digital Outputs 41 工 ntegrity Monitor⊥ ng and Failure Warning Outputs 41 3.6.1 General Master warning d Roll Warning output 6.3.1 Primary Pitch and Roll Failure Warning Output Auxiliary Pitch and Roll Warning Output on1t。 r Inte宫rty 3。63.4 Failure Warning delays 43 3.6.4 Heading Warning output 3.6.5 HSI Warning output 43B 3.6.6 Digital Data Warning Output 43B 3.6.7 omparison Warning 3.7 工 NS Equipment Accuracy 43B 3.8 工Ns工 nter-Commundcations System 3.9 INS Inter-System Comparison INS Steering signal 4。0 STANDARD SIGNAL CHARACTERISTICS 47-71 General Ac d operating ra 4,1.1 Resolution Standardized Output signal Synchro standards 47&49 rd Applied Voltage 49 signal 49 4,1.2.4 Phase Reversing Voltage Standards 4。2 51 4。2.1 titude and Longitude 51 4,2。1。1 Manua】工nput 51 4,2。1 Automatic Data Input No, 3(Possible Future Function) 51 4.2。2 Section numb Used 4,2。3 Head1 51 Altitude 51 4、2。4.1 Analog Signal 51 4。2.4.2 Provisions for Future Digital Signal 5 True Airspeed (TAS) 53 g Voltage (Standard Ir 53 4。2。5。2 Synchro (Alternative Input For Retrofit Installations) 53 a:3:52 KIFIS Synchro (Non ARINC) DADS Data B 4.2.6 General Purpose Binary Data Input 53B 4.2.7 Ea±1 ure Warning Inputs 53B Outputs 55 Position 4。3。1.1 BGD Output 4.3.1.2 Binary Output (Sera1) 4.3.2 frue Heading and Platform Azimuth 4。3.2。1 Analog Output 55 4。3.2.2 BCD and Binary outputs of True Heading g 55 4.3.3 Pitch 57 4。3。3。1 General 57 4.3.3.2 Output No. 1 57 4。3.3.3 Outputs No. 2 and 3 57 Output No. 4 (Tt 57 4.3.3.5 Output No. 5(Two-Wire) 57 士r 0307b1?0003244■ 里 ABLE OF CONTENT(ont!d) REVISED: February 1, 1973 REPLACEMENT PAGE SECTION SUBJECT PAGE NO Roll 59 43.4. Genera王 59 4。3。4。2 output N。1 59 4。3。4.3 Output No, 2 and 3 59 4。3。4。4 Output No, 4(Iwo-Wire 9 .3,4。5 Output No. 5 (Two-Wireh 43。4。5.10 utput No,4(200Mv0°茆 4.34·5420 utput No.6(200Me30 4。3.5 Track Angle (Ik) 43。5。1 Analog Output 61 4。3。5。2 Dig⊥ tal Output8 61 4,3.6 Ground Speed 61 Distance-to-Go (DIs 63 4。3.8 I1me-to-Go (TIME) 63 4。3。9 Wnd Angle 63 4、3。10 Wind Speed 63 4。3.11 Cro8 s Track D⊥ stance 63 4。3。12 Track Angle Error (TK E) 63 4.3.12,1 Analog Output 63 43.12。2 D1gia工0uput 63 4.3。13 Drift Angle (DA 65 4. 3.13.1 Analog Output 65 4。3.13.2 Digital Output 65 43.14 Des⊥ red Track 65 4.3。15 Align Statua 65 4。315。1 Align Status 65 4。3。15。2 Waypoint 4.3.16 N→ s and E-W Velocit 65 4,37 Vertical Acceleration (customer Optional Output) 67 4,3.18 P1 afOrm▲ azimuth 67 4,3.19 Cross Track devation 67 4。3.19.1 Level Dc signal 67 4.3.19.2 3 High Level DC Signal -See Supplement No.1 67 4;3。20 Fro 4.3.21 Drlft Angle plus Track Angle Error 4.3.22 Failure Warning Outputs 4.3.22.1 Master Warning 69 4.3.22.2 Primary Warning 4,3.22.3 Aux⊥1 ary Warm⊥ng 9 4。3.23 Alert light 71 /4,3。24 Steering Signal (Roll Command) 4。3,25 (Autopilot Up Elevator"signa1 71 Along Track Horizontal Acceleration(customer option Output) 71 50 BAS工c卫工 GITAL SIGNAL STANDARD8 73 Basic seria1 Data Transm⊥B⊥ on standard8 73 Basic Transmission Syst Data Transmission Circuit 73 5.1,3 Word Synchranizat⊥on 73 75 75 5。2.1 Word structure 75 5。2.2 nguage 52.2.1 B式 Coded Decimal (B 75 5.2.2.2 75 5。23 Special Code Assignment for Direction and Status Designation 77 5,2.3。1 General 77 5.2.3.2 BCD De8 nation Matr⊥x 5.2.3.3 Binary Designat⊥ on matr⊥跑eg g 79 fransmission orde 79 Electrical Characteristics 5.4.1 DC Signaling with Non-Return-to-Zero Logic 79 Signal Logic Level Digital Transmitter 79 55,1 Output Load Capab土1ty Electro-Magnetic Nolee Rejection 81 Reverse Current Capabilit 81 Digital Receiver 81 Input Load Characteristics Electro-Magnetic Noise Refection Data Circuit Switching 83 Remote display dew 83 ■037b17001日25占 LSED: June 30. 1972 SECTION SUBJECT 卫AGEo Ge 1 83 58.2 Primary Power Label/Address Recognition 5.8.4 Failure Warning Indication ed Data Diaplay 5.8.6 Input工8o⊥aton Display Dimming Control 5.87.1 Solid State Indicator Dimming 85 5,8.7,2 Electro-Mechanical Displays 85 、 6。0 NAVIGATION UNIT DESIGN 6。2 Mounting Rigidity 7。0 ELECTRONICS S DESIGN 89 7。1 General 89 7。2 Time-Shared Digital-to-Analog (D/A)Co inverter 89 Time Shared Digital Outputs 89 7.4 t Figure of Merit Output工ao_at CONTROL/DISPLAY 8.1 General 91 Data Loading 8。2。1 Pugh Buttons 91 Pairing o￡or 91 8.4 Discrete Push Button Controle 93 Display Dimmers 8.6 Pane工11 mination 8。7 Polarity of Displayed Information 93 8。8 Display Legibility 9.0 MODE SELECTOR UNIT DESIGN 9。L Genera1 92 Mode Selector Switch Functional Teat Swtich (Optional) 95 9。4 Ready-Nav Light 9 BAtT Warning Light Panel Illumination 10.0 REMOTE CONTROL AND DISPLAY UNIT DESIGN 10.1 LIST OF ATTACHMENTS AN ATTAGHMEAT TT起 NOTES APPLICABLE TO THE INS STANDARD INTERWIRING 2-1 STANDARD INTERHIRINO 2-2 ETANDARD工 NTERWIRING 101 8 INS DLANRORMANLELECTRONTCS UNIS- PIN ASSIGNMENTS (LEFT HAND PLUGS) 102 3-2 (RIGHT HAND PLUGS) INS NAVIGATION UNIT- FORM FACTOR 104 3-4 OUNTING DIMENSIONS AND TOLERANCES 105 DELETED 106 INS PLATFORM MDUNT 107 BATTERY UNIT FORM FACTOR 108 456777 INPUTS AND OUTPUTS 109 INS SYNCHRO EXCITATION 130 INS CONTROL/DISPLAY UNIT PIN ASSIGNMENTS 131 1 (PUSH BUTTON CONTROLS) 112 I(SELECTOR SWITCH-PUSH BUTTON CONTROLS) nR函T￠ NTROL DI8 PLAY UNITS(ARA四址s 114 INS MODE SELECTOR PANEL PIN ASSIGNMENT TORM FACTOR 116 FUTURE COMPASS COUPLER SYSTEN 10-1 CUSTOMER NEEDS FOR ATTITUDE OUTPUT ISOLATION 118-120 10-2 ATTITUDE OUTPUT ISOLATION NEEDS 11-1 POSSIBLE INSTRUMENTATION CONFIGURATIONS USING BASIC INS OUTPUTS 11-2 TYPICAL INSTRUMENTATION SINGLE SERVO(EXISTING)HSI 11-3 TYPICAL INSTRUMENTATION FOR TRACK ANGLE BASIC DISPLAY ON THREE SERVO (NEW)HSI 123 TYPICAL INSTRUMENTATION- USE OF DRIFT ANGLE PLUS TRACK ANGLE ERROR (NEW THREE 12 SUMARY OF DIGITAL OUTPUT STANDARDS 124" 12-2 〗 GITAL SIGNAL TIMLNG SIGNAL TIMING TOLERANCES 126 BCD CODE ASSIGNMENTS 32-5 工NABL/ ADDRESS CODE AS8述N3 128-128c 12-5-1 ARINC 575 DADS LABEL/ADDRESS CODE ASSIGNMENTS 工 NS INPU& UTPUT CIRCUIT STANDARDS! 129 TYPICAL EXAMPLES OF STANDARD BINARY DATA EXPRESSED IN TNO'S COMPLEMENT FRACTIONAL NOTATION 130 LOGIC LEVEL WAVEFORMS 131 ARINC BCD DIGITAL WORD STRUCTURES APPLICABLB TO CHARACTERISTICS 561, 131A 568,AND575 INS T COMPUTER BUS POWER 132 INTERCHANGE OF DATA BETWEEN INS SYSTEMS 33 John Mary SIGNAL PHASE REVERSAL FOR TWo-WIRE PITCH ROLL OuTputs 133A ANDX王 DIAGRAM0玉 NS TERMLNOL0 134 APPENDIX2 DOPPLER RADAR NAVIGATION NOMENCLATURE (EXTRACTED FROM ARINC CHARACTERISTIC 543)138137 ApPENDIX 1 DIS CUSSION OF INS TERMINOLOGY PROBLRMS 135 APPENDIX X-1 CHRONOLOGY OF AEEC INS NEWSLETTERS 139-141 PBXX2 INS SUBC四踞 ETING PARTI GTPANES 142-144 AR工NC551-175■口307b]?001己B TNTENTTONALIY LEFT BLANK l1 ARINO5b1-175■日307]700012?T□ OMENTARY o0 The "Commentary, and its significance in this Characteristic It will be no ted that the Specification material in thi a document is on the right hand pages. The Commentary on the left hand pages is to provide further explanation to the reader with respect to the airline industry desires During the courge of evolving the final ARINC Equipmment Characteristic, the left hand commentary undergoes numerous revisions in order to remain consistent with the revised Spec, material and the supplementary guidance expressed by the airlines and the manufacturers. Most of the material in the Commentary is in- tended to remain there after the Characteriatic is finalized and published as an Induatry-approved document, however, some portions of the Commentary may be applicable to only one or two drafts and deletion i9 necessary before the docu- ment18f1na1ly且8ued .l This Spec Covera Basic INS System There has been a considerable amount of discussion concerning the appropriate s cope of an airline inertial navigation system, The arguments have rangedfrom one extreme of a Spec, limited to just the stabilized platform to the other ex- treme of a gigantic central digital processor aystem which would integrate (or just plain mix upl )the inertial navigation system with about everything else in the aircraft especially in the ssT 'sl This good natured conflict has existed primarily between the computer designers ( who seem to have a flarefor integrating everything into one giant economy sized computer which allegedly will never-ever faill )and the airlines who can recall no thing but bitter memories of multipleintegration when applied ta systems planning spica⊥。 f the pract1 al problems empha日2 ed by the ai21ne818 the diapatch requirement imposed upon that portion of the inertial system invo lved in pro viding attitude signals when thig information is used for the pilots: primary f11 ght disp.1ay日·A里a1eot1 function preclude日 dispatch of the aircraf七 until the source of trouble can be isolated and the necesaary equipment replaced. Needless to say, the airlines envision a much greater trouble shooting problem when a large central digital processor is involved ---to say nothing of the magnitude of the spares and equipment replacement problems In spite of the pressure tending to push the industry toward one extreme or the o ther, the airlines have moved in the direction of a reasonable minimum package I for the basic inert.1 navigation sensor and steering compυ uter system.。工七i8 anticipa ted this equipment will be used in some installations with additional computer capability, which may be configured more easily to meet the cus? individual operational needs, where more sophisticated navigation computation is needed 1.2 Advantages of Uniform Operational Procedures In discussing the INS System Modes of Operations and the diaplay unit layout,the airlines emphasize the sizeable economic advantages offered b y uniform operational change in equipment requirea what might be considered a trivial amount of additio bl procedures. For example, one airline cited a recent case where an apparently "mind al pilot training, This additional training amounted to one hour per pilot(all two thousand of them)multiplied by $1100 per hour of flight time --a rather princely sum to pay for a "minori variation!! I These airlines comments should not be misconstrued by the equipment designer as an indication that all airlines have exactly the same operational needs. However, it does provide clear guidance of themagnitude of the penalties assoc l with unique operational procedures thinh matt mean11+ in nice", but not fully essential design features in the I1. and system operation.

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