ARINC 707-7-2009 RADIO ALTIMETER《无线电高度表1978.含补充件1-7》.pdf

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1、 AN DOCUMENT Prepared by AEEC Published by AERONAUTICAL RADIO, INC. 2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401-7435 RADIO ALTIMETER ARINC CHARACTERISTIC 707-7 PUBLISHED: April 6, 2009 This document is published information as defined by 15 CFR Section 734.7 of the Export Administration Regulations (E

2、AR). As publicly available technology under 15 CFR 74.3(b)(3), it is not subject to the EAR and does not have an ECCN. It may be exported without an export license. DISCLAIMER THIS DOCUMENT IS BASED ON MATERIAL SUBMITTED BY VARIOUS PARTICIPANTS DURING THE DRAFTING PROCESS. NEITHER AEEC, AMC, FSEMC N

3、OR ARINC HAS MADE ANY DETERMINATION WHETHER THESE MATERIALS COULD BE SUBJECT TO VALID CLAI MS OF P ATENT, COPYRIG HT OR OT HER PRO PRIETARY RIGHTS BY THIRD PARTIES, A ND NO RE PRESENTATION OR WARRANTY, E XPRESS O R IMPLIED, IS MADE IN THIS REGARD. ARINC I NDUSTRY ACT IVITIES US ES RE ASONABLE E FFOR

4、TS TO DEVELOP A ND MAINTAIN THESE DOCUMENTS. HOWEVER, NO CERTIFICATION OR WARRANTY IS MADE AS TO THE TECHNICAL ACCURACY OR SUFFICIENCY OF THE DOCUMENTS, THE ADEQ UACY, MERCHANT ABILITY, FITNESS FOR INT ENDED PURPOSE OR SAFETY OF A NY PRODUCTS, COMPONENTS, OR S YSTEMS DESIGNED, TESTED, RATED, INSTALL

5、ED OR OPERATED IN ACCORDANCE WITH ANY ASPECT OF THIS DOCUMENT OR T HE ABSENCE OF RI SK OR HAZARD ASSOCIATED WITH SUCH PRODUCTS, COMPO NENTS, OR S YSTEMS. T HE USER OF T HIS DO CUMENT ACKNOWLEDGES THAT IT SHALL BE SOLELY RESPONSIBLE FOR ANY LOSS, CLAIM OR DAMAGE THAT IT MAY INCUR IN CONNECTION WITH I

6、TS USE OF OR RELIANCE ON T HIS DOCUMENT, AND SHALL HOLD ARINC, AEEC, AMC, F SEMC AND ANY PARTY THAT PARTICIPATED IN THE DRAFTING OF THE DOCUMENT HARMLESS AGAINST ANY CLAIM ARISING FROM ITS USE OF THE STANDARD. THE USE IN THIS DOCUMENT OF AN Y TERM, SUCH AS SHALL OR MUST, IS NOT INTENDED T O AFFECT T

7、HE ST ATUS OF T HIS DOCUME NT AS A VOLUNT ARY STANDARD OR IN ANY WAY T O MODI FY T HE ABOVE DIS CLAIMER. NOT HING HEREIN SHA LL BE DE EMED T O REQUIRE A NY P ROVIDER OF EQUIP MENT TO INCORPORATE ANY ELEMENT OF THIS STANDARD IN ITS PRODUCT. HOWEVER, VENDORS WHICH REPRESENT THAT THEIR PRODUCTS ARE COM

8、PLIANT WITH THIS STANDARD SHALL BE DEEMED ALSO TO HAVE REPRESENTED THAT THEIR PRODUCTS CONTAIN OR CONFORM TO THE FEATURES THAT ARE DESCRIBED AS MUST OR SHALL IN THE STANDARD. ANY USE O F OR RE LIANCE ON T HIS DO CUMENT SHALL CONSTITUTE A N ACCEPTANCE THEREOF “AS IS” AND BE SUBJECT TO THIS DISCLAIMER

9、. 2009 BY AERONAUTICAL RADIO, INC. 2551 RIVA ROAD ANNAPOLIS, MARYLAND 21401-7435 USA Prepared by the AEEC Characteristic 707 Adopted by the AEEC Executive Committee May 3, 1978 Summary of Document Supplements Supplement Adopti on Date Published Characteristic 707-1 December 7, 1978 March 20, 1979 Ch

10、aracteristic 707-2 June 18, 1980 August 6, 1980 Characteristic 707-3 March 12, 1981 April 3, 1981 Characteristic 707-4 December 10, 1981 January 29, 1982 Characteristic 707-5 November 4, 1982 January 17, 1983 Characteristic 707-6 January 3, 1985 February 6, 1985 Characteristic 707-7 March 2, 2009 Ap

11、ril 6, 2009 A description of the changes introduced by each supplement is included on goldenrod paper at the end of this document. ARINC CHARACTERISTIC 707-7 RADIO ALTIMETER Published: April 6, 2009 ii FOREWORD Aeronautical Radio, Inc., the AEEC, and ARINC Standards ARINC organizes aviation industry

12、 committees and participates in related industry activities that benefit aviation at large by providing technical leadership and guidance. These activities directly support aviation industry goals: promote safety, efficiency, regularity, and cost-effectiveness in aircraft operations. ARINC Industry

13、Activities organizes and provides the secretariat for international aviation organizations (AEEC, AMC, FSEMC) which coordinate the work of aviation industry technical professionals and lead the development of technical standards for airborne electronic equipment, aircraft maintenance equipment and p

14、ractices and flight simulator equipment and used in commercial, military, and business aviation. The AEEC, AMC, and FSEMC develop consensus-based, voluntary standards that are published by ARINC and are known as ARINC Standards. The use of ARINC Standards results in substantial benefits to the aviat

15、ion industry by allowing avionics interchangeability and commonality and reducing avionics cost 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 Char

16、acteristics indicate to prospective manufacturers of airline electronic equipment the considered and coordinated opinion of the airline technical community concerning the requisites of new equipment including standardized physical and electrical characteristics to foster interchangeability and compe

17、tition. b) ARINC Specifications Are principally used to define either the physical packaging or 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, ofte

18、n related to avionics maintenance and support. The release of an ARINC Standard does not obligate any organization 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 endo

19、rsement of any manufacturers product designed or built to meet the ARINC Standard. In order to facilitate 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 Stan

20、dard. An ARINC IA Project Initiation/Modification (APIM) form solicits any recommendations for addition of substantive material to this volume which would be the subject of a new Supplement. ARINC STANDARD 707 TABLE OF CONTENTS iii 1.0 INTRODUCTION AND DESCRIPTION .1 1.1 Purpose of this Characterist

21、ic 1 1.2 Function of the Equipment .1 1.3 Unit Description1 1.3.1 Receiver - Transmitter Unit .1 1.3.2 Indicators.2 1.3.3 Antennas .2 1.3.4 Control Panel.2 1.4 Interchangeability.2 1.4.1 General Requirements for Interchangeability2 1.4.2 “Generation Interchangeability” Considerations2 1.4.3 Intercha

22、ngeability Desired for the ARINC 707 Radio Altimeter.3 1.5 Regulatory Approval 3 1.6 Reliability3 1.7 Applicable Publications, Specifications and Reports .4 2.0 INTERCHANGEABILITY STANDARDS 5 2.1 Introduction 5 2.2 Form Factors, Connectors however, such antennas are not universally applicable to oth

23、er aircraft types which are quite restrictive with respect to depth projection within the aircraft. Furthermore, although the dimensional standards of Attachment 9 are likely to remain the industry standard for some time to come, a trend must be expected in the direction of small antennas for those

24、applications where space is critical. Accordingly, the standard dimensions and form factors set forth in Attachment 10 have been established for the smaller antenna. 2.3 Interwiring The standard interwiring to be installed for the radio altimeter is set forth in Attachment 2. This interwiring is des

25、igned to provide the degree of interchangeability specified in Section 1.4, and manufacturers are cautioned not to rely upon special wires, cabling, or shielding for use with particular units because they will not exist in the standard installation. This characteristic does not retain the synchroniz

26、ation wires between radio altimeters in multiple system installations provided in earlier ARINC characteristics. COMMENTARY The standardized interwiring is perhaps the heart of all ARINC Characteristics. It is this feature which allows the airline customer to complete his negotiations with the airfr

27、ame manufacturer so that the latter can proceed with engineering and initial fabrication prior to airline commitment on a specific source of equipment. This provides the equipment manufacturer with many valuable months in which to put the final “polish” on his equipment in development. The readers a

28、ttention is directed to the interwiring guidance in ARINC Report 414, Section 5.0. This material defines all of the basic standards utilized in airframe wiring installations, and all equipment manufacturers should make themselves familiar with it. The reader is also cautioned to give due considerati

29、on to the specific notes in Attachment 1 as they apply to the standard interwiring. 2.4 Power Circuitry 2.4.1 Primary Power Input The equipment should be designed to use 115 volt (10%) 380 to 420 Hz single phase AC power. When required by the manufacturer, the equipment can also be powered by +28 Vd

30、c. This primary power will be protected by a single circuit breaker, normally situated in the aircraft power distribution center, of the size shown in Attachment 2. ARINC CHARACTERISTIC 707 Page 8 2.0 INTERCHANGEABILITIY STANDARDS The aircraft power supply characteristics, utilization, equipment des

31、ign limitations, and general guidance material are set forth in ARINC Report 413A: Guidance for Aircraft Electrical Power Utilization and Transient Protection. COMMENTARY The airframe manufacturers have expressed a desire (the age old one!) to select the circuit breaker size solely on the basis of w

32、ire protection with no regard for the secondary protection of equipment. The users strongly encourage the use of a suitable, reliable breaker of the smaller value to serve both protection objectives. 2.4.2 Power Control Circuitry There should be no master on/off power switching within the radio alti

33、meter and power should be wired directly to the equipment from the circuit breaker panel. 2.4.3 Indicator Power The radio altimeter indicators should operate from 115 Vac. This power may be provided by the R/T unit (unless the R/T unit is powered by 28 Vdc) or by a separate circuit breaker. 2.4.4 Th

34、e Common Ground The wires designated as “Common Ground” (or as chassis ground) are used for the DC ground return to the aircraft structure and may be grounded to the chassis of the equipment if the manufacturer so desires. In any event, they will be grounded to the aircraft structure. They should no

35、t be used as common returns for any circuits carrying AC currents. 2.4.5 The AC Common Cold Although the AC Common Cold lead will eventually reach a ground on the aircraft distribution bus, there are often high common mode currents involved in such circuits or aircraft structure. Thus, manufacturers

36、 should not assume that the “AC Common Cold” will represent a solid ground. 2.4.6 Transients The radio altimeter should be designed to operate without interruptions in data output and without failure warning indications throughout the duration of primary power transients specified in RTCA DO-160. Li

37、kewise, the installation designer should provide power having no interruption in excess of those defined in DO-160. COMMENTARY The users, especially the autoland equipment, have experienced nuisance failure warning indications, altitude data interruptions and display “irregularities” due to past inc

38、ompatibility between the quality of electrical power provided and needed by the radio altimeter. A major objective in the preparation of DO-160 was to preclude these problems with future equipment. ARINC CHARACTERISTIC 707 Page 9 2.0 INTERCHANGEABILITY STANDARDS 2.5 Standard Outputs The desired inte

39、rchangeability for the radio altimeter in Section 1.4 necessitates standardization of the output interface parameters. The R/T should provide two ARINC 429 low speed digital data buses. The one identified in Attachment 2 as Altitude Bus No. 1 is intended for the exclusive use of the Automatic Flight

40、 Control System (AFCS). The other “Altitude Bus No. 2” is intended for use by the displays and all other systems including secondary inputs to the AFCS. The digital word structure is set forth in ARINC 429 with typical examples shown in Attachment 13. The users have considered a number of proposals

41、and concluded the ARINC 707 Radio Altimeter should NOT provide analog outputs, altitude rate outputs, or altitude trip outputs (except for the DH Alert, DH + Delta H Alert, and H Alert as described in Sections 4.11.1, 4.11.2, and 4.11.3). Therefore, no such outputs or even “RESERVED” pins have been

42、provided. COMMENTARY Altitude Bus No. 1 output should be designed to meet the ten-to-the-ninth numerical analysis exercise described in Section 3.10.3. 2.6 Environmental Conditions The radio altimeter should be tested environmentally in terms of the requirements of RTCA DO-160: Environmental Conditi

43、ons and Test Procedures for Airborne Equipment. Attachment 12 to this characteristic tabulates the relevant environmental categories. 2.7 Cooling The radio altimeter should be designed to accept, and airframe manufacturers should configure the installation to provide, forced air cooling as defined i

44、n ARINC Specification 600. The standard installation should provide an air flow of 7.7 Kg/hr of air having a maximum temperature of 40C. This value is calculated on the basis of a maximum of 35W of dissipated energy in the R/T unit. The pressure drop of the coolant airflow through the equipment shou

45、ld be 5 3 mm of water. The radio altimeter should be designed to expend this pressure drop to maximize the cooling effect. Adherence to the pressure drop standard is needed to allow interchangeability of equipment. An internal blower should not be provided. COMMENTARY Equipment failures in aircraft

46、due to inadequate thermal management have been a problem for the airlines for many years. In Section 3.5 of ARINC Specification 600, they have documented some things they believe airframe and equipment suppliers need to know to prevent such problems in the future. Aircraft equipment manufacturers ar

47、e strongly encouraged to review this guidance. ARINC CHARACTERISTIC 707 Page 10 2.0 INTERCHANGEABILITIY STANDARDS 2.8 Grounding and Bonding The attention of equipment and airframe manufacturers is drawn to the guidance material in Section 3.2.4 and Appendix 1 of ARINC Specification 600 on the subjec

48、t of equipment and radio rack grounding and bonding. 2.9 Location of R/T Unit in Aircraft The R/T unit may be positioned in an aircraft central radio rack or in some other location as dictated by the minimum and maximum Aircraft Installation Delay (AID) values which are established as 40 feet and 80

49、 feet respectively as defined in Section 2.10. Regardless of the R/T unit location, as selected by the installation designer, the cooling prescribed in Section 2.7 above should be provided. In fact, most customers have indicated they will insist! 2.10 Aircraft Installation Delay (AID) Selection The R/T unit should, for standardization reasons, be shop adjusted for the 57-foot standard AID calibration. However, to permit use of the 40 foot and 80 foot AID calibrations, programming pins should be of proper jumpers on the rear connector, the desired AID calibration of 40 fee