1、 AN DOCUMENT Prepared by AIRLINES ELECTRONIC ENGINEERING COMMITTEE Published by AERONAUTICAL RADIO, INC. 2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401-7435 HEAD-UP DISPLAY (HUD) SYSTEM ARINC CHARACTERISTIC 764 PUBLISHED: July 8, 2005 This document is based on material submitted by various participants d
2、uring the drafting process. Neither AEEC nor ARINC has made any determination whether these materials could be subject to valid claims of patent, copyright or other proprietary rights by third parties, and no representation or warranty, express or implied, is made in this regard. Any use of or relia
3、nce on this document shall constitute an acceptance thereof “as is” and be subject to this disclaimer. 2005 BY AERONAUTICAL RADIO, INC. 2551 RIVA ROAD ANNAPOLIS, MARYLAND 21401-7435 USA Prepared by the Airlines Electronic Engineering Committee Characteristic 764 Adopted by the Airlines Electronic En
4、gineering Committee April 26, 2005 ARINC CHARACTERISTIC 764 HEAD-UP DISPLAY (HUD) SYSTEM Published: July 8, 2005ii FOREWORD Aeronautical Radio, Inc., the AEEC, and ARINC Standards Aeronautical Radio, Inc. (ARINC) was incorporated in 1929 by four fledgling airlines in the United States as a privately
5、-owned company dedicated to serving the communications needs of the air transport industry. Today, the major U.S. airlines remain the Companys principal shareholders. Other shareholders include a number of non-U.S. airlines and other aircraft operators. ARINC sponsors aviation industry committees an
6、d participates in related industry activities that benefit aviation at large by providing technical leadership and guidance and frequency management. These activities directly support airline goals: promote safety, efficiency, regularity, and cost-effectiveness in aircraft operations. The Airlines E
7、lectronic Engineering Committee (AEEC) is an international body of airline technical professionals that leads the development of technical standards for airborne electronic equipment-including avionics and in-flight entertainment equipment-used in commercial, military, and business aviation. The AEE
8、C establishes consensus-based, voluntary form, fit, function, and interface standards that are published by ARINC and are known as ARINC Standards. The use of ARINC Standards results in substantial benefits to airlines by allowing avionics interchangeability and commonality and reducing avionics cos
9、t by promoting competition. There are three classes of ARINC Standards: a) ARINC Characteristics Define the form, fit, function, and interfaces of avionics and other airline electronic equipment. ARINC Characteristics indicate to prospective manufacturers of airline electronic equipment the consider
10、ed and coordinated opinion of the airline technical community concerning the requisites of new equipment including standardized physical and electrical characteristics to foster interchangeability and competition. b) ARINC Specifications Are principally used to define either the physical packaging o
11、r mounting of avionics equipment, data communication standards, or a high-level computer language. c) ARINC Reports Provide guidelines or general information found by the airlines to be good practices, often related to avionics maintenance and support. The release of an ARINC Standard does not oblig
12、ate any airline or ARINC to purchase equipment so described, nor does it establish or indicate recognition or the existence of an operational requirement for such equipment, nor does it constitute endorsement of any manufacturers product designed or built to meet the ARINC Standard. In order to faci
13、litate the continuous product improvement of this ARINC Standard, two items are included in the back of this volume: An Errata Report solicits any corrections to the text or diagrams in this ARINC Standard. An ARINC IA Project Initiation/Modification (APIM) form solicits any recommendations for addi
14、tion of substantive material to this volume which would be the subject of a new Supplement. ARINC CHARACTERISTIC 764 TABLE OF CONTENTS iii 1.0 INTRODUCTION .1 1.1 Purpose and Scope .1 1.2 Relationship to Other Documents 1 1.3 Functional Overview 2 1.3.1 HUD Computer2 1.3.2 HUD Projection Unit 2 1.3.
15、3 HUD Combiner2 1.3.4 HUD Pilot Input Device3 1.3.5 HUD Annunciation Device.3 1.4 Interchangeability.3 1.4.1 Interchangeability of HUD Components.3 1.4.2 Generation Interchangeability Considerations .4 1.5 Regulatory Approval 4 1.6 Integrity and Availability .4 1.7 Reliability .4 1.8 Testability 5 1
16、.9 Flight Simulators5 2.0 INTERCHANGEABILITY STANDARDS.6 2.1 Introduction6 2.2 HUD Computer 6 2.2.1 Form Factor, Connector and Index Pin Coding6 2.2.2 Weight.7 2.2.3 Cooling7 2.2.4 Power Circuitry7 2.2.5 Environmental Conditions .8 2.2.6 Grounding and Bonding 9 2.3 HUD Projection Unit 9 2.3.1 Form F
17、actor and Connectors.9 2.3.2 Weight.10 2.3.3 Cooling10 2.3.4 Power Circuitry10 2.3.5 Environmental Conditions .11 2.3.6 Grounding and Bonding 11 2.4 HUD Combiner 11 2.4.1 Form Factor and Connectors.12 2.4.2 Weight.12 2.4.3 Cooling13 2.4.4 Power Circuitry13 ARINC CHARACTERISTIC 764 TABLE OF CONTENTS
18、iv 2.4.5 Environmental Conditions .13 2.4.6 Grounding and Bonding 13 2.5 HUD Pilot Input Device .13 2.5.1 Form Factor and Connectors.13 2.5.2 Weight.13 2.5.3 Cooling13 2.5.4 Power Circuitry14 2.5.5 Environmental Conditions .14 2.5.6 Grounding and Bonding 14 2.6 HUD Annunciation Device14 2.6.1 Form F
19、actor and Connectors.14 2.6.2 Weight.15 2.6.3 Cooling15 2.6.4 Power Circuitry15 2.6.5 Environmental Conditions .15 2.6.6 Grounding and Bonding 15 3.0 SYSTEM DESIGN CONSIDERATION.16 3.1 HUD System Configurations 16 3.1.1 Single HUD Federated Architecture 16 3.1.2 Twin HUD Federated Architecture.16 3.
20、1.3 Twin HUD Federated Architecture.17 3.1.4 Integrated HUD Federated Architecture 18 3.2 Unit Identification Considerations.18 3.3 Data Loading .18 3.3.1 Data Loader Interface18 3.3.2 Data Loadable Software Elements 19 3.3.2.1 Operational Program Software (OPS).19 3.3.2.2 Operational Program Config
21、uration (OPC) .19 3.3.2.3 Operational Program Database (OPD) .19 3.3.3 Configuration Control 19 3.4 HUD Accuracy .19 3.5 Growth.20 3.5.1 Populated Growth .20 3.5.2 Unpopulated Growth .20 3.6 Crew Data Input and Mode Controls21 3.6.1 Data Entry.21 3.6.1.1 MCDU Data Entry.21 3.6.1.2 HCP Data Entry21 A
22、RINC CHARACTERISTIC 764 TABLE OF CONTENTS v 3.6.2 Mode Selection .21 3.6.2.1 MCDU Mode Selection .21 3.6.2.2 HCP Mode Selection 21 3.7 Flight Crew Indication 22 3.7.1 Alerting22 3.7.2 System Status.22 3.8 Certification Considerations .23 3.9 Data Recording23 4.0 HUD FUNCTIONS .28 4.1 Basic Functions
23、 .28 4.1.1 Approach and Rollout Guidance28 4.1.2 Takeoff Guidance28 4.1.3 Primary Flight Information .28 4.2 Functional Growth28 4.2.1 Enhanced Vision System (EVS) 29 4.2.2 Synthetic Vision System (SVS) .29 4.2.3 Surface Guidance .29 4.2.4 HUD Use As a Primary Flight Display .29 5.0 INTERFACES AND P
24、ROTOCOL.30 5.1 Introduction30 5.2 HUD Computer Inputs and Outputs .30 5.2.1 Analog Input Signals .30 5.2.2 Discrete Input Signals .30 5.2.2.1 Type 1, Ground/Open Analog Discrete Input Signal30 5.2.2.2 Type 2, 28 Vdc/Open Analog Discrete Input Signal 31 5.2.3 Discrete Output Signals 31 5.2.3.1 Type 1
25、, Ground/Open Analog Discrete Output Signal.31 5.2.3.2 Lamp Driver Output Signal31 5.2.4 ARINC 429 Data Bus 31 5.2.4.1 ARINC 429 Input Buses31 5.2.4.2 ARINC 429 Output Buses.32 5.2.5 RS-232 Data Bus 32 5.2.6 Ethernet Connections32 5.2.6.1 Quadrax Ethernet Connections.32 5.2.6.2 Standard Ethernet Con
26、nections32 5.2.7 Coaxial Interfaces .32 5.2.7.1 Coaxial Inputs.32 ARINC CHARACTERISTIC 764 TABLE OF CONTENTS vi 5.2.7.2 Coaxial Outputs33 5.2.8 Video Interface33 5.2.8.1 Fiber Optic Inputs .33 5.2.8.2 Fiber Optic Outputs 33 5.2.9 Airplane Personality Module (APM).33 5.2.10 HUD Computer Interface to
27、Overhead Disconnect 34 5.3 HUD Overhead Disconnect Panel Signals .35 5.3.1 Power Connections .35 5.3.2 Other Connections 35 5.4 HUD Annunciator Panel 35 5.4.1 Discrete Input Signals .35 5.4.2 Discrete Output Signals.35 5.4.3 Program Pin Inputs .35 5.4.4 Bright Dim Input 35 5.4.5 ARINC 429 Data Bus 3
28、6 5.4.5.1 ARINC 429 Inputs.36 5.4.5.2 ARINC 429 Outputs36 5.5 HUD Control Panel Inputs and Outputs36 5.5.1 Analog Discrete Input Signals .36 5.5.2 Analog Discrete Output Signals.36 5.5.3 Program Pin Inputs .36 5.5.4 ARINC 429 Data Bus 37 5.5.4.1 ARINC 429 Inputs.37 5.5.4.2 ARINC 429 Outputs37 6.0 BU
29、ILT-IN TEST AND MAINTENANCE PROVISIONS38 6.1 Genera.38 6.2 Fault Detection and Reporting .38 6.2.1 Centralized Fault Reporting Interface 39 6.3 Ramp Maintenance and Return Service Testing39 6.4 System Configuration Management.40 6.5 Provisions for Automatic Test Equipment.41 6.6 Shop Maintainability
30、.41 6.7 HUD Configuration Verification 41 ATTACHMENTS 1 Acronyms List 42 2 Standard Interwiring.45 3A HUD Computer Connector Rear View46 ARINC CHARACTERISTIC 764 TABLE OF CONTENTS vii 3B HUD Computer Pin Assignment Zonal Allocation47 3B HUD Computer Pin Assignment Insert A Top Left Plug48 3B HUD Com
31、puter Pin Assignment Insert B Middle Left Plug .49 3B HUD Computer Pin Assignment Insert C Bottom Left Plug 50 3B HUD Computer Pin Assignment Insert D Top Right Plug .51 3B HUD Computer Pin Assignment Insert E Middle Right Plug .52 3B HUD Computer Pin Assignment Insert F Bottom Right Plug.53 3C HUD
32、Overhead Disconnect Pin Assignment 54 3D HUD Control Panel Connector Pin Designations56 3E HUD Annunciator Panel (HAP) Connector Pin Assignment Optional.57 3F HUD Computer Connector Signal Analysis 58 4 Alignment and Boresighting Considerations.60 5 Environmental Test Categories63 6 ARINC 429 Data F
33、ormats 64 7 EVS Interface Considerations 68 8A ARINC 600 Size Connector Archive.71 8B HUD Computer Pin Assignment Insert A Top Plug.72 8B HUD Computer Pin Assignment Insert B Middle Plug 73 8B HUD Computer Pin Assignment Insert C Bottom Plug .74 ARINC Standard Errata Report ARINC IA Project Initiati
34、on/Modification (APIM) Guidelines for Submittal ARINC CHARACTERISTIC 764 - Page 1 1.0 INTRODUCTION 1.1 Purpose and Scope This document describes a Head-Up Display (HUD) system for installation in all types of aircraft. It describes the physical form factors, fit dimensions, electrical interface defi
35、nition and typical HUD functions. The HUD system provides primary flight, navigation and guidance information to the pilot in the forward field of view. The HUD accomplishes this by projecting images onto a combiner positioned in front of the pilot. The displayed image is collimated (appears at infi
36、nity to the pilot) and conformal (some of the symbology overlays the outside view). The conformal nature of the symbology presented to the pilot allows the pilot to see flight information and guidance cues together with the outside world visual cues. The system displays sufficient data to enable the
37、 flight crew to control the aircraft, particularly in low visibility operations. 1.2 Relationship to Other Documents This Characteristic defines HUD functionality, protocols, and equipment interfaces. The latest versions of the following documents may apply. ARINC Report 413B: Guidance for Aircraft
38、Electrical Power Utilization ARINC Specification 429: Mark 33 Digital Information Transfer System (DITS) ARINC Specification 600: Air Transport Avionics Equipment Interfaces ARINC Report 604: Guidance for Design and Use of Built-In Test Equipment ARINC Report 607: Design Guidance for Avionic Equipme
39、nt ARINC Report 609: Design Guidance for Aircraft Electrical Power Systems ARINC Report 610B: Guidance for Use of Avionics Equipment and Software in Simulators ARINC Report 615: Airborne Computer High-Speed Data Loader ARINC Report 615A: High-Speed Data Loading Using Ethernet Interface ARINC Report
40、624: Onboard Maintenance System ARINC Report 651: Design Guidance for Integrated Modular Avionics ARINC Specification 664: Aircraft Data Network ARINC Report 665: Loadable Software Standards ARINC Report 667: Guidance for the Management of Field Loadable Software (FLS) ARINC Characteristic 739A: Mul
41、ti-Purpose Control and Display Unit RTCA DO-178 /EUROCAE ED-12: Software Considerations in Airborne Systems and Equipment Certification ARINC CHARACTERISTIC 764 - Page 2 1.0 INTRODUCTION RTCA DO-160 /EUROCAE ED-14: Environmental Conditions and Test Procedures for Airborne Equipment SAE AS8034: Minim
42、um Performance Standard for Airborne Multipurpose Electronic Displays SAE AS8055: Minimum Performance Standard for Airborne Head-Up Display SAE ARP 5288: Transport Category Aircraft Head-Up Display Systems 1.3 Functional Overview The HUD system is used for a wide variety of flight guidance functions
43、 available to the flight deck crew in all phases of flight, including takeoff and landing. HUD provides visual aid for airport surface operations. The HUD should be designed with sufficient growth capability and should be expandable to embrace additional functions. The HUD system components generall
44、y include: HUD Computer HUD Projection Unit (HPU) HUD Combiner HUD Pilot Input Device HUD Annunciation Device COMMENTARY This section describes the basic functions of HUD components. Depending on the specific installation, the HUD functions may be integrated with each other or integrated with other
45、aircraft systems. 1.3.1 HUD Computer The HUD computer receives information from various aircraft systems and sensors. From information received, it provides display formats to the HPU/combiner. 1.3.2 HUD Projection Unit The HUD Projection Unit (HPU) fits into the aircraft at the pilots crew station(
46、s). It contains an image generation device and drive circuitry as well as the optical system. Together, these produce the image and project it onto the HUD combiner. 1.3.3 HUD Combiner The HUD combiner is a transparent optical surface with a semi-reflective coating, mounted forward of the pilot. The
47、 image projected from the projection unit reflects toward the pilot while the forward view remains visible through the combiner. The combiner thus “combines” the real-world image with the image projected by the HPU. ARINC CHARACTERISTIC 764 - Page 3 1.0 INTRODUCTION COMMENTARY Generally, there are t
48、wo basic configurations of HPU and combiner. HPU is mounted above the pilots head and projects the image onto the combiner mounted in the pilots forward line of sight. In this configuration, the HPU and combiner are often separate units. HPU is mounted within the aircraft glare shield and projects t
49、he image onto the combiner mounted in the pilots forward line of sight. In this configuration, the HPU and combiner are often one unit. 1.3.4 HUD Pilot Input Device The HUD pilot input device may be used to control the HUD and to manually enter data required by the HUD system. The pilot input device should be integrated into an existing control and display device, such as a Multi-Purpose Control and Display Unit (MCDU) or other aircraft control panels. COMMENTARY The pilot input device may be implemented a
