ARINC 703-2-1983 Thrust Control Computer System《推进控制计算机包括附录1到2》.pdf

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1、THRUST CONTROL COMPUTER SYSTEM ARINC CHARACTERISTIC 703-2 PUBLISHED: OCTOBER 31,1983 Prepared by AIRLINES ELECTRONIC ENGINEERING COMMITTEE Published by AERONAUTICAL RADIO, INC. 2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401 This document is based on material submitted by various participants during the d

2、rafting 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 reliance on this

3、 document shall constitute an acceptance thereof “as is” and be subject to this disclaimer. Characteristic 703 Characteristic 703 Characteristic 703-1 Characteristic 703-2 Copyright 1998 by AERONAUTICAL RADIO, INC. 255 1 Riva Road Annapolis, Maryland 24101-7465 USA ARINC CHARACTERISTIC 703-2O THRUST

4、 CONTROL COMPUTER SYSTEM ARINC Characteristic 703-2 was fist published on: October 31, 1983 Prepared by the Airlines Electronic Engineering Committee Adopted by the Airlines Electronic Committee: Adopted by Industry: Adopted by the Airlines Electronic Engineering Committee: Adopted by the Airlines E

5、lectronic Engineering Committee: December 7, 1978 March 1, 1979 June 19, 1980 December 10, 198 1 FOREWORD Activities of AERONAUTICAL RADIO, INC. (ARINC) and the Purpose of ARINC Characteristics Aeronautical Radio, Inc. is a corporation in which the United States scheduled airlines are the principal

6、stockholders. Other 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 land radio stations, the fulfillment of systems requirements

7、to accomplish ground and airborne compatibility, the allocation and assignment of frequencies to meet those needs, the coordination incident to standard airborne compatibility, the allocation and assignment of frequencies to meet those needs, the coordination incident to standard airborne communicat

8、ions and electronics systems and the exchange of technical information. ARINC sponsors the Airlines Electronic Engineering Committee (AEEC), composed of airline technical personnel. The AEEC formulates standards for electronic equipment and systems for the airlines. The establishment of Equipment Ch

9、aracteristics is a principal function of this Committee. An ARINC Equipment Characteristic is finalized after 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, an

10、d 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 exi

11、stence of an operational requirement for such equipment, nor does it constitute endorsement of any manufacturers 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 equip

12、ment the considered opinion of the airline technical people, coordinated on an industry basis, concerning requisites of 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 whi

13、ch influence interchangeability of equipment without seriously hampering engineering initiative. ii AHINC C HAHACI1.: It ISI IC 703 ITEM 1 .o 1.1 1.2 1.3 1.3.1 1.3.2 1.3.3 1.3.4 1.3.5 1.3.6 1.3.7 1.3.8 1.3.9 1.4 1.5 2.1 2.2 2.0 2.2.1 2.2.2 2.3 2.4 2.4.1 2.4.2 2.4.3 2.4.4 2.5.1 2.5 2.5.1.1 2.5.1.2 2.

14、6 2.7 2.8 3.0 3.1 3.2 3.3 3.3.1 3.3.2 3.4 3.5 3.5.1 3.5.2 3.5.3 3.5.4 3.5.5 3.5.6 3.5.7 3.6 3.6.1 3.6.2 3.6.3 3.7 4.0 4.1 4.1.1 4.1.2 4.1.2.1 4.1.2.2 4.1.2.3 4.1.2.4 4.1.2.5 TABLE OF CONTENTS SUBJECT INTRODUCTION AND DESCRIPTION Purpose of this Document General System Description Unit Description Th

15、rust Control Computer AFS Controller Thrust Rating Panel Annunciator Unit Autothrottle Disconnect Switches Go-Around Initiation Switches Throttle Actuator Unit Throttle Clutch Statushaintenance Panel Interchangeability Regulatory Approval INTERCHANGEABILITY STANDARDS Introduction Form Factor, Connec

16、tors and Index Pin Coding Thrust Control Comnuter Unit (TCCU) Thrust Rating PanelL Intenviring Power Circuitry Primary Power Input Power Control Circuitry The Common Ground The AC Common Cold Environmental Conditions Thermal Interface and Design TCCU Thrust Rating Panel Weights System Functions and

17、Signal Characteristics Grounding and Bonding SYSTEM DESIGN CONSIDERATIONS Basic Philosophy Configuration Adaptive Desi n Centralized Administrative dntrol Autothrottle Controller Thrust Rating Panel Function vs. Modes Function Description Thrust Rating Computation and Display Autothrottle Flight Env

18、elo e Protection Thrust Contro? During Non-Stabilized Flight Phases Other Optional Capabilities Engine Trimming Function Test and Maintenance Mode Description Autothrottle Modes Thrust Rating Computation Modes Autothrottle and Thrust Rating Computation Mode Compatibility Autothrottle Arm Circuit STA

19、NDARD SIGNAL CHARACTERISTICS General Accuracy and Operating Ranges Resolution Standard Signals Synchro Standards AC Signal Standards Standard “Ground” Signal Standard “Open” Signal Standard “Applied” Voltage PAGE 1 1 1 2 2 3-4 4 4 4 4 4 4 4 4 4 4-5 6 6 6 6 6 6 6 6 6 6 6-7 7 7 7 7 7 7-8 8 8 8 9 9 9 9

20、 9 9 9 9 9 . 111 TABLE OF CONTENTS (contd) ITEM 4.1.3 4.1.4 4.2.1 4.2.2 4.2.3 4.2.4 4.2 4.2.4.1 4.2.4.2 SUBJECT PAGE 9 9 9 9 9 9 10 10 10 10 10 10 10 10 10 4.2.4.4 4.2.5.4 4.2.5 4.2.5.5 4.2.6 4.2.7 4.2.7.4 4.2.8 4.2.9 4.2.11 4.2.12 4.2.10 4.2.13 4.3 4.3.1 4.3.1.1 4.3.1.2 4.3.2 4.3.3 4.3.4 4.3.5 4.3.

21、6 4.3.7 5.0 5.1 5.2 5.3 5.3.1 5.3.2 6.0 6.1 6.2 6.2.1 6.2.2 ATTACHMENTS 2 2A 3 4 5 6 7 8 APPENDIX 1 The Common Ground The AC Common Cold System Inputs IRS or AHRS Bus Air Data System Bus Radio Altimeter Bus Engine Sources N1 or EPR Fuel Flow EngineT pe Throttle %urCes Go Around Switches Autothrottle

22、 Disconnect Switches Clutch Power Input Airfiame Sources Landin Gear Flight !ontrol Computer System Flight Management Computer System Autothrottle Controller Output Bus Thrust Rating Panel Output Bus Flight Envelope Limit Detection Discrete Stahidchange Over Signal Input System Outputs Control Servo

23、 Out uts Individual Clutch 8ommand Servo Power Control Autothrottle Armed Switch Thrust Rating Limit Bug Output External Discrete Warning Flight Envelope Limit Detection Discrete Stahidchange Over Signal Output Drag Demand Signal TCCS CONTROLLER DESIGN General Autothrottle Controller Thrust Rating P

24、anel Form Factors and Connector Panel Illumination PROVISIONS FOR AUTOMATIC TEST EQUIPMENT General Unit Identification Pin Allocation Use of ATLAS Language Notes Applicable to Standard Interwiring Thrust Ratin Controller Interwiring ARINC 703 kandard Interwiring 10 11 11 11 11 11 11 11 11 11 11 11 1

25、1 11 11 12 12 13 13 13 13 13 13 14 14 14 14 14 15 16 17-22 Diagram 23 Environmental Test Categories 24 TCCU Input/Output 25 Thrust Control Computer Unit 26 Thrust Rating Panel 27 TCC BNR Digital Inputs 28 TCC BNR Digital Outputs 29 TCC BCD Digital Outputs 30 Identical Input/Output for Corresponding

26、Unit of the Two Architectures 31 Bibliography Of The AEEC ARINC 703 Thrust Control Computer System 3 1-34 (TCCS) Project iv ARINC CHARACTERISTIC 703 - Page 1 1.0 INTRODUCTION AND DESCRIPTION 1.1 Pmose of this Document This document sets forth the characteristics of the Thrust Control Computer System

27、 (TCCS) portion of the larger Automatic Flight System (AFS). The intent of this document is to provide general and specific design guidance for the development and the installation of a TCCS primarily for airline use. This document will make reference to and state need for assumptions or prerequisit

28、es for the Flight Control Computer System (FCCS) and the Flight Management Computer System (FMCS), but those elements will be defiied in separate ARINC Characteristics. As such, this guidance will include the desired operational capability of the system and the standards necessary to ensure intercha

29、ngeability. Equipment manufacturers should note that this document encourages them to produce maintenance-fiee, high- performance equipment, rather than that of minimal weight and dimensions. They are at liberty to accomplish this objective by means of design techniques they consider to be the most

30、appropriate, as their airline customers are interested primarily in the end result rather than the means employed to achieve it. 1.2 General Svstem Description The functions of the autoflight system are distributed between: The Flight Augmentation Computer System (FACS) The Flight Control Computer S

31、vstem (FCCS) The Fright Management Cmputer System (FMCS) The Thnist Control Computer System (TCCS) The TCCS basically provides the functions associated with the throttle control. The FCCS, FMCS and TCCS are amenable to form, fit and function standardization. ARINC Equipment Characteristics 701, 702

32、and 703 are devoted respectively to them. To obtain a cost effective system design which takes into account airline maintenance logistics, manufacturing advantages of batch production, intelligent marketing efforts and other benefits of prudent standardization an effort has been made in this documen

33、t to defiie a “configuration tolerant” system partitioning concept whereby the standard computer (or part number identified LRU) can be used interchangeably in an architecture using 1,2 or 3 FCCU and O, 1 or 2 FMCU: - either in the “BASIC FMC” architecture in which FMCS provides autopilot and autoth

34、rottle outer loop functions and mode which are not associated with LAND mode. 2.1 General Svstem Description (contd) As far as TCCS is concerned, this is accomplished by providing the TCCU with the necessary number of inputs and outputs. When any mention in this 703 TCCS Characteristic is unique to

35、one architecture, this will be indicated by the reference of the relevant architecture. In such a case, a commentary will indicate in which other Characteristic the possible corresponding mention is provided. 1.3 Unit Description 1.3.1 Thrust Control Computer (TCCU) The Thrust Control Computer Unit

36、should house all of the components, electronic circuitry, etc. . ., incident to the functioning of the system, including the circuitry for processing sensor inputs. In addition, this unit should originate all of the outputs defined in sections 3 and 4 of this document. 1.3.2 AFS Controller The AFS C

37、ontroller will provide means for mode selection and control functions to the FCCS and the TCCS. This Controller is described in ARINC Characteristic 70 1. 1.3.3 Thrust Rating Panel The Thrust Rating Panel should provide the means for mode selection and Control Thrust rating functions to the TCCS. Fu

38、rther details are contained in Section 5.0 of this document. This panel also provides displays of other parameter as described in Section 3.3.2. 1.3.4 Annunciator Unit The Annunciator Unit described in ARINC Characteristic 701 should provide means for informing the crew of the selected FCCS and TCCS

39、 modes and the operational status of the system. COMMENTARY These switches operate logic circuitry in the TCCU to cause the autothrottle to behave as if the system were disconnected as long as the automatic flight envelope protection limits have not been exceeded. All TCCS operation, automatic and o

40、therwise, is suspended by the operation of the Autothrottle Armed Switch (see Section 4.3.2). Section 3.7 Autothrottle Arm Circuit provides a description of this circuit. Inasmuch as this equipment may be subject to different operational requirements of various users, this circuit is brought out int

41、o the aircraft interwiring where it may be modified without changing the black box equipment. (See diagram in Attachment 5.) - or in the “OPTIONAL FMC” architecture in which FCCS and TCCS are composed of “stand alone” units respectively devoted to surfaces and throttles controls (further details may

42、 be found in Attachment 8). ARINC CHARACTERISTIC 703 - Page 2 1.0 INTRODUCTION AND DESCRIPTION (contd) 1.3.5 Autothrottle Disconnect Switches Two switches should be located on the two outer-most throttle levers in such a manner that either the pilot or the copilot can easily disconnect the autothrot

43、tle manually while grasping the throttle levers. These switches should deselect the current autothrottle mode but should not disarm the autothrottle. 1.3.6 Go-Around Initiation Switches The Go-Around Initiation Switches are provided as a means for initiating the Go-Around function in the TCCS and in

44、 the FCCS. COMMENTARY Switches may be provided for take off initiation. These take off initiation switches may be common to the Go-Around initiation switches. 1.3.7 Throttle Actuator Unit Because of the “limited” interchangeability (see Section 1.5) it is impossible to standardize Form and Fit of th

45、e throttle actuator. However rate feed back signal is standardized in Section 4. 1.3.8 Throttle Clutch A clutch of either the magnetic solenoid or irreversible “mechanical diode” type (such as a “Sprag” type of mechanism) should be provided to insure adequate isolation between the servo drive mechan

46、ism and each individual throttle run when Autothrottle is not engaged. Further, the clutch system should include some means which will allow the pilot physically to overpower the Autothrottle in the event of an emergency. In installations which use an engaging clutch, such as the magnetic types, it

47、will be necessary to include a “slip clutch” or equivalent. Up to four separate outputs may be provided to permit optional individual manual override of engine throttles by selective declutching on command of force sensors mounted on the throttles. 1.3.9 StahdMaintenance Panel The Statushaintenance

48、Panel described in ARINC Characteristic 70 1 will provide status maintenance information for the TCCS and FCCS. 1.4 Interchangeabilitv System interchangeability if specified in this ARINC Characteristic for the TCCU, Thrust Rating Panel and Throttle Actuator, regardless of the manufacturing source.

49、The standards necessary to ensure this interchangeability are set forth in Section 2 of this Characteristic. The definition of “system” interchange-ability is as stated in Section 2 of ARINC Report 403, “Guidance for Designers of Airborne Electronic Equipment”. Because of the complex nature of the TCCS and the number of multiple interfaces with other sub-systems, a further breakdown in categories of interchangeability has been adopted for this specification. The categories of “System Interchangeability” as they stand now in ARINC Characteristic 701 are: 1.4 Interchangeabilitv (con