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1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication m
3、ay be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: 724-776-4970 (outside USA)
4、 Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org AIR4367 REV. A AEROSPACE INFORMATION REPORT Issued 1995-04 Revised 2007-07 Superseding AIR4367 (R) Aircraft Inflight Ice Detectors and Icing Rate Measuring Instruments RATIONALE Rationale for revising this document w
5、as driven by the need to harmonize it with the more recently issued SAE document AS5498, and to provide technical updates. AS5498 defines minimal operational specifications for inflight icing detection systems, whereas this document provides guidance information on ice detection technologies and app
6、lications. TABLE OF CONTENTS 1. SCOPE3 1.1 Purpose.3 2. REFERENCES3 2.1 Applicable Documents 3 2.1.1 SAE Publications.3 2.1.2 U.S. Government Publications3 2.1.3 Other Publications.4 2.2 Other Applicable References4 2.3 Definitions .5 2.4 Abbreviations 7 3. ICING INSTRUMENTATION CLASSIFICATIONS.7 3.
7、1 Flight Icing Detection Systems8 3.2 Aerodynamic Performance Monitoring System 8 3.3 Classification by Sensing Method.8 4. ICE DETECTION METHODS.8 4.1 Visual 8 4.1.1 Daytime.8 4.1.2 Nighttime.9 4.2 Obstruction9 4.3 Differential Pressure .9 4.4 Latent Heat9 4.5 Vibration9 4.6 Microwave.11 4.7 Electr
8、omagnetic (EM) Beam Interruption14 4.8 Pulse-Echo (Ultrasonic)14 4.9 Capacitance or Total Impedance14 4.10 Optically Occluding .15 4.11 Optically-refractive 15 4.12 Advanced Concepts16 4.12.1 Infrared16 4.12.2 Thermal Flow 16 4.12.3 Ultrasonic16 5. DESIGN GUIDANCE 16 Copyright SAE International Prov
9、ided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:42:36 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR4367 Revision A - 2 - 5.1 Environmental Conditions.17 5.1.1 Ambient Temperature .17 5.1.2 Altitude 17 5.1.3 Li
10、quid Water Content 17 5.1.4 Drop Size 17 5.1.5 Erosion, Hail Impact, and Bird Strike17 5.2 Functional Requirements18 5.2.1 Airspeed18 5.2.2 Sensitivity18 5.2.3 Ice Protection18 5.2.4 False Signal 18 5.2.5 Fail-Safe Design18 5.3 Reliability and Credibility.18 5.3.1 Primary Detection Systems.18 5.3.2
11、Advisory Ice Detection Systems .19 5.4 Installation.19 5.4.1 Location Considerations .19 5.4.2 Other Installations.20 5.5 Verification 20 5.6 Emerging Operating Considerations.20 5.6.1 SLD and Ice Crystals 20 5.6.2 Freezing Fraction21 6. UNIQUE REQUIREMENTS21 6.1 Engine Inlets .21 6.2 Rotorcraft 21
12、7. NOTES22 FIGURE 1 SELF-CONTAINED, ENGINE-INLET ICE DETECTOR (B-1B AIRCRAFT) USING LATENT HEAT PRINCIPLE10 FIGURE 2 SELF-CONTAINED B-747/B-767 ICE DETECTOR USING MAGNETOSTRICTIVE VIBRATORY PRINCIPLE .12 FIGURE 3 MD-11 ICE DETECTOR SYSTEM USING MAGNETOSTRICTIVE VIBRATION PRINCIPLE (SENSING PROBE ASS
13、EMBLY LEFT, SIGNAL CONDIONER ASSEMBLY RIGHT)13 FIGURE 4 FLUSH-MOUNTED MD-80 WING UPPER SURFACE ICE DETECTOR USING A PIEZOELECTRIC VIBRATED DIAPHRAGM .13 FIGURE 5 FLUSH-MOUNTED ICE DETECTOR USING A MAGNETOSTRICTIVE VIBRATED DIAPHRAGM.14 FIGURE 6 DUCTED OPTICALLY OCCLUDING ICE DETECTOR SYSTEM15 FIGURE
14、 7 REFRACTIVE- BASED ICE DETECTING TRANSDUCER15 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:42:36 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR4367 Revision A - 3 - 1. SCOPE
15、 This document provides information regarding ice detector technology, design and operating requirements. The SAE document AS5498 provides detailed information regarding the requirements, specifications, qualification, and certification of icing detection systems. This document is not meant to repla
16、ce AS5498 but to enhance it by considering unique aspects of sensing technology and in particular those that may not be certificated at the time of this revision. To that end an effort has been made not to duplicate information contained in AS5498. Icing rate information is included where applicable
17、. The primary application is associated with ice forming on the leading edges of airfoils and inlets while the aircraft is in flight. Information related to detection of ice over cold fuel tanks and icing at low velocity operation is included. The material is primarily applicable to fixed-wing aircr
18、aft. Unique requirements for engine inlets and rotorcraft are also provided. 1.1 Purpose The purpose of this document is to provide information regarding various in situ icing sensing technologies and issues a user of these technologies should consider regarding the method of operation, performance,
19、 design, verification, and installation of aircraft ice detectors and icing rate indicators. The intent is not to duplicate AS5498 but to supplement it in areas that may not have been deemed appropriate for such a standards document. 2. REFERENCES 2.1 Applicable Documents The following publications
20、form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited he
21、rein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. Many of the referenced documents are available online. 2.1.1 SAE Publications Available from SAE International, 400 Commonwea
22、lth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org. AIR1168/4 SAE Aerospace Applied Thermodynamics Manual, Ice, Rain, Fog, and Frost Protection AS5498 Minimum Operational Performance Specification for In-flight Icing Detection S
23、ystems AIR5504 Aircraft Inflight Icing Terminology 2.1.2 U.S. Government Publications 2.1.2.1 U.S. Department of Defense (DOD) Publications Available from the Document Automation and Production Service (DAPS), Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697-6257, http:/as
24、sist.daps.dla.mil/quicksearch/. MIL-HDBK-310 Global Climatic Data for Developing Military Products MIL- HDBK-5400 Electronic Equipment, Airborne, General Guidelines for MIL-STD-704F Aircraft Electrical Power Characteristics Copyright SAE International Provided by IHS under license with SAELicensee=D
25、efense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:42:36 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR4367 Revision A - 4 - 2.1.2.2 U.S. Department of Transportation, Federal Aviation Administration (FAA) Publications Available from Federal Aviation Admini
26、stration, 800 Independence Avenue, SW, Washington, DC 20591, Tel: 866-835- 5322, www.faa.gov. The FAA Icing Handbook is available through National Technical Information Service, 5285 Port Royal Road, Springfield, VA 22161, Tel: 800-553-6847 or 703-605-6000, www.ntis.gov. Advisory Circular 20-73A, Ai
27、rcraft Ice Protection, August 16, 2006 Title 14 of the US Code of Federal Regulations, Part 23 Airworthiness Standards: Normal Category Airplanes (14 CFR Part 23) Title 14 of the US Code of Federal Regulations, Part 25 Airworthiness Standards: Transport Category Airplanes (14 CFR Part 25) Title 14 o
28、f the US Code of Federal Regulations, Part 27 Airworthiness Standards: Normal Category Rotorcraft (14 CFR Part 27) Title 14 of the US Code of Federal Regulations, Part 29 Airworthiness Standards: Transport Category Rotorcraft (14 CFR Part 29) Title 14 of the US Code of Federal Regulations, Part 33 A
29、irworthiness Standards: Aircraft Engines (14 CFR Part 33) DOT/FAA/CT-88/8-l, “Aircraft Icing Handbook,“ March 1991 2.1.3 Other Publications 2.1.3.1 AGARD Publications Available from http:/www.rta.nato.int/. AGARD Advisory Report No. 127 Aircraft Icing, November 1978 AGARD Advisory Report No. 166 Rot
30、orcraft Icing - Status and Prospects, August 1981 AGARD Advisory Report No. 223 Rotorcraft Icing - Progress and Potential, September 1981 2.1.3.2 RTCA Publications Available from Radio Technical Commission for Aeronautics Inc., 1828 L Street, NW, Suite 805, Washington, DC 20036, Tel: 202-833-9339, w
31、ww.rtca.org. RTCA DO-160D Environmental Conditions and Test Procedures for Airborne Equipment, July 29, 1997 RTCA DO-178B Software Considerations in Airborne Systems and Equipment Certification, December 1992 RTCA DO-254 Design Assurance Guidance for Electronic Hardware, April 2000 2.2 Other Applica
32、ble References American Meteorological Society Glossary of Meteorology, 2001 (available from American Meteorological Society, Boston, MA) Cober, S.G., G.A. Isaac and A.V. Korolev: Assessing the Rosemount icing detector with in-situ measurements. J. Atmos. Oceanic Tech., 18, 515-528, 2001 Eurocontrol
33、, Aeronautical Information Manual, October 1996 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:42:36 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR4367 Revision A - 5 - Hansman,
34、 R. J. Jr. and Kirby, M. S., Real Time Measurement of Ice Growth During Simulated and Natural Icing Conditions Using Ultrasonic Pulse-Echo Techniques, AIAA Paper 86-0410, January 6-9, 1986 Jackson , D.G., D.J. Cronin, J.A. Severson and D.G. Owens: Ludlam Limit Considerations on Cylinder Ice Accretio
35、n: Aerodynamics and Thermodynamics, AIAA-2001-0679, 39th Aerospace Sciences Meeting for engine inlets, temperatures above 10 C (50 F). NONINTRUSIVE: Flush with the aerodynamic surface causing no disturbance to the flow field. OUTSIDE AIR TEMPERATURE (OAT): The static temperature of the ambient frees
36、tream air (outside the aircraft). PIEZOELECTRIC: The property of a material (usually ceramic) that causes it to change dimensions and vibrate when subjected to a high frequency electric field. In ice detectors, the shift in resonant frequency is used to indicate ice buildup. REFERENCE SURFACE: The s
37、urface where a FIDS sensor makes its measurement (e.g., the intrusive part of a probe system). ROTORCRAFT: Aircraft powered by a rotor operating approximately in a horizontal plane or an aircraft where the rotor can be moved from a horizontal plane to a vertical plane. They are also known as helicop
38、ters, rotary wing aircraft or tiltrotor aircraft. (Some distinguishing features pertinent to ice detection are low forward velocity and rotor downwash.) SENSITIVITY: The ability to detect slight amounts (or slight differences in amounts) of ice accretion. STRATIFORM CLOUDS: A cloud species character
39、ized by a flattened appearance and spread out in an extensive horizontal layer; low, middle, or high level layer clouds, characterized by extensive horizontal rather than vertical development (from FAAIH). Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/
40、5913977001 Not for Resale, 12/04/2007 19:42:36 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR4367 Revision A - 7 - STRATUS: A low level ( 6500 ft) STRATIFORM CLOUD with a uniform, gray, sheet-like appearance resembling fog. No turbulence, but can create serious ici
41、ng due to distance (from FAAIH). 2.4 Abbreviations AGARD Advisory Group for Aerospace Research and Development AIAA American Institute of Aeronautics and Astronautics AIR Aerospace Information Report (SAE) AIM Aeronautical Information Manual AISLIS Advanced Icing Severity Level Indicating System AMS
42、 American Meteorological Society APMS Aerodynamic Performance Monitoring System AS Aerospace Standard (SAE) BIT Built-in-test CFR Title 14 of the US Code of Federal Regulations DOT Department of Transportation EM Electromagnetic FAA Federal Aviation Administration FAAIH FAA Icing Handbook FIDS Fligh
43、t Icing Detection System FPD Freezing point depressant LWC Liquid water content MED Mean effective diameter MTBF Mean time between failure MVD Median volumetric diameter NACA National Advisory Committee for Aeronautics NASA National Aeronautics and Space Administration NRC National Research Council
44、OAT Outside air temperature RTCA Radio Technical Commission for Aeronautics TAT Total air temperature TM Technical memorandum UFR Undetected failure rate m Micrometer or micron (one-thousandth millimeter) 3. ICING INSTRUMENTATION CLASSIFICATIONS Icing instrumentation systems provide information to t
45、he flight crew and/or airplane systems concerning inflight icing. Components of the system may be intrusive or non-intrusive to the airflow. The system may be directly or indirectly sensitive to the physical phenomena of inflight icing. Icing instrumentation systems are divided into two types: Fligh
46、t Icing Detection Systems (FIDS) and Aerodynamic Performance Monitoring Systems (APMS). FIDS are further divided into those that detect ice accretion and those that detect icing conditions. These definitions have been taken from and are consistent with AS5498. Further clarification of these terms ca
47、n be found in AS5498, sections 1.4 and 1.5. Icing instrumentation systems may include a processing unit to perform signal processing, sensor monitoring, data communication, or other functions. The processing unit may either be integrated with or separate from the sensor(s). Icing instrumentation sys
48、tems may be connected to a device to provide information to the cockpit crew and/or communicate with other onboard equipment or systems. Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:42:36 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR4367 Revision A - 8 - 3.1 Flight Icing Detection Systems A FIDS that detects ice accretion informs the flight crew an