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 theref
2、rom, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions.Copyright 2016 SAE InternationalAll rights reserved. No part of this publi
3、cation may 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: +1 724-776-4970 (out
4、side USA)Fax: 724-776-0790Email: CustomerServicesae.orgSAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedbackon this Technical Report, please visithttp:/www.sae.org/technical/standards/ARP5672AEROSPACERECOMMENDED PRACTICEARP5672Issued 2009-12Reaffirmed 2016-04Aircraft Precipita
5、tion Static CertificationRATIONALEARP5672 has been reaffirmed to comply with the SAE five-year review policy.FOREWORD Whenever a reference document appears in this Recommended Practice, it carries the minimum revision level of the reference document acceptable to meet the intended requirements. Late
6、r versions of the reference document are also acceptable but earlier versions are not acceptable. In all cases, other documents shown to be equivalent to the reference document are also acceptable. TABLE OF CONTENTS 1. SCOPE . 3 2. RELATED DOCUMENTS . 3 2.1 FAA Advisory Circulars (AC) . 3 2.2 SAE Pu
7、blications . 4 2.3 Military Documents 4 2.4 Other Publications . 4 2.5 Definitions and Acronyms . 4 2.5.1 Definitions . 4 2.5.2 Acronyms 5 3. BACKGROUND 6 4. P-STATIC PROTECTION DESIGN AND COMPLIANCE 6 5. DEFINE AIRCRAFT CONFIGURATION, OPERATING CONDITIONS AND MATERIALS . 6 6. ESTABLISH THE AIRCRAFT
8、 P-STATIC CHARGING ENVIRONMENT . 7 6.1 Aircraft Environment 7 6.2 Rotorcraft Environment . 8 7. DESIGN AIRCRAFT P-STATIC PROTECTION . 8 7.1 Design of Aircraft Structure and Parts 8 7.1.1 Electrical Bonding of Exposed Structure or Parts . 9 7.1.2 Non-Conducting Structures or Parts . 10 7.1.3 Windows
9、and Window Heat Systems . 10 7.2 Design Method for P-Static Dischargers . 10 7.2.1 Static Discharger Complement and Locations . 10 7.2.2 Characteristics of Static Dischargers 14 7.2.3 Discharger Types and Construction . 14 7.2.4 Discharger Mounting Methods 15 7.2.5 Static Discharger Qualification an
10、d Characteristics 16 8. VERIFY P-STATIC PROTECTION EFFECTIVENESS 16 8.1 Similarity Assessment . 17 8.2 Test . 17 8.2.1 Surface Bonding Verification . 17 8.2.2 P-Static Ground Tests . 17 8.2.3 Surface Charge Application 19 8.2.4 Noise Detection . 19 8.2.5 Examples of Noise Generating Items Found Duri
11、ng Ground Test. 20 8.2.6 Aircraft P-Static Flight Tests . 20 8.3 Analysis . 21 9. IMPLEMENT CORRECTIVE MEASURES . 21 10. MAINTENANCE 21 10.1 Maintenance Definitions 22 10.2 Maintenance Procedures 23 10.2.1 Control of Bonding Straps and Leads . 23 10.2.2 Control of Surface Coating 23 10.2.3 Control o
12、f Static Dischargers 24 10.2.4 Control of Panel Bonding 24 10.3 Configuration Deviation List (CDL) . 24 FIGURE 1 - STATIC DISCHARGER LAYOUT (BEECH 1900D) . 12 FIGURE 2 - STATIC DISCHARGER LAYOUT (CESSNA 525C) . 13 FIGURE 3 - STATIC DISCHARGER LAYOUT (CESSNA 750) . 13 FIGURE 4 - STATIC DISCHARGER LAY
13、OUT (777) . 14 FIGURE 5 - STATIC DISCHARGER COMPONENTS . 15 FIGURE 6 - STATIC DISCHARGER WICK COMPONENTS . 15 FIGURE 7 - STATIC DISCHARGER RETAINER . 16 FIGURE 8 - P-STATIC GROUND TEST FLOW . 18 FIGURE 9 - COTTON AND CARBON/NYLON WICK STATIC DISCHARGERS 28 FIGURE 10 - NICHROME/MICROPOINT STATIC DISC
14、HARGERS . 28 FIGURE 11 - CARBON (COMPOSITE TIP) STATIC DISCHARGER 29 FIGURE 12 - NULL-FIELD (ORTHO-DECOUPLED) STATIC DISCHARGER 29 FIGURE 13 - TRAILING TYPE NULL FIELD STATIC DISCHARGER . 29 TABLE 1 - PRECIPITATION PARTICLE PARAMETERS FOR SUBSONIC AIRCRAFT 8 TABLE 2 - ELECTROSTATIC DISCHARGE TYPES A
15、ND PREVENTION 9 TABLE 3 - STATIC DISCHARGER COMPLEMENT 11 TABLE 4 - STATIC DISCHARGER CHARACTERISTICS (FROM MIL-STD-9129E) 16 SAE INTERNATIONAL ARP5672 2 OF 291. SCOPE Aircraft surface precipitation static (p-static) charge can be generated when aircraft fly through ice particles, rain, snow and dus
16、t. However, in the context of p-static protection, this document is used for providing guidance for any thing that charges the outer surface of the aircraft (e.g. engine exhaust). P-static discharges from the aircraft can disrupt aircraft communication, navigation, and surveillance radios, and can d
17、amage aircraft radomes and windshields. This SAE Aerospace Recommended Practice (ARP) defines design considerations for aircraft p-static control and related methods to verify acceptable aircraft p-static performance. This ARP addresses p-static charging due to the aircraft flying through ice partic
18、les, rain, snow and dust. It does not address other triboelectric charging that may be present in an aircraft, such as triboelectric fuel charging or environmental control system or air conditioning static charging. It does not address electrostatic charging created by passengers or crewmembers, or
19、electrostatic discharge hazards to electronics and systems. The purpose of this document is to provide information and guidance concerning an acceptable means, but not the only means, of compliance with Parts 23, 25, 27, and 29 (23.867, 25.899, 27.610, and 29.610) of the Federal Aviation Regulations
20、 (FAR) and European Aviation Safety Agency (EASA), applicable to aircraft for protection against the adverse effects of precipitations static. This ARP provides general information on aircraft surface p-static charging mechanisms and the impact p-static has on aircraft systems. It addresses elements
21、 of effective aircraft p-static control design. Finally, it defines methods for verifying acceptable aircraft p-static control. Accordingly, this material is neither mandatory nor regulatory in nature and does not constitute a regulation. Aircraft p-static control should be addressed early in the ai
22、rcraft design to be effective. Effective aircraft design features and effective verification methods will result in an aircraft that can be operated in p-static charging conditions without adverse impact to the aircraft systems. The existing reports and guidance do not provide standards for aircraft
23、 design to control p-static or standard methods to verify acceptable aircraft p-static control. This document provides acceptable approaches to design effective aircraft p-static control, and provides acceptable methods to verify the design effectiveness. Existing aircraft certification regulations
24、in Title 14 CFR 25.899, 27.610(d) and 29.610(d), specifically address aircraft p-static control. These regulations include the requirement to minimize the accumulation of electrostatic charge in order to reduce to an acceptable level the effects of static electricity on the functioning of essential
25、electrical and electronic equipment. Compliance may be shown by bonding the components to the airframe, or incorporating other acceptable means to dissipate the static charge. Title 14 CFR 23 is an exception, as it does not specifically address aircraft p-static control, however p-static is consider
26、ed a foreseeable operating condition, so all aircraft designed for operation in instrument meteorological conditions (IMC) should have certified p-static control. Prior to this document, the absence of specific standards or guidance material resulted in inconsistent application and verification of t
27、he requirements for aircraft p-static control. 2. RELATED DOCUMENTS 2.1 FAA Advisory Circulars (AC) Available from the US Department of Transportation; Subsequent Distribution Office; Ardmore East Business Center; 3341 Q 75th Avenue; Landover, MD 20785 AC 23.1309-1C System Design and Analysis AC 25.
28、899-1 Electrical Bonding and Protection Against Static Electricity AC 25.1309-1A System Design and Analysis AC 27.1B Certification of Normal Category Rotorcraft AC 29.2C Certification of Transport Category Rotorcraft SAE INTERNATIONAL ARP5672 3 OF 292.2 SAE Publications Available from SAE Internatio
29、nal, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org ARP1870 Aerospace Systems Electrical Bonding and Grounding for Electromagnetic Compatibility and Safety 2.3 Military Documents Available from the Document Auto
30、mation and Production Service (DAPS), Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697-6257, http:/assist.daps.dla.mil/quicksearch/. MIL-DTL-9129E Dischargers, Electrostatic, General Specification for MIL-STD-464A Environmental Effects, Requirements for Systems 2.4 Other P
31、ublications J. E. Nanevicz, Precipitation Charging and Corona-Generated Interference in Aircraft, SRI Technical Report 73, 1961, Stanford Research Institute J. E. Nanevicz, Precipitation Charging and Corona-Generated Interference in Aircraft, SRI Technical Report 77 Project 2494, 1968, Stanford Rese
32、arch Institute J. P. Glecier, Aircraft Static Discharger Analysis Technique, 1999 International Conference on Lightning and Static Electricity (ICOLSE), SAEP-99/344,1999-01-2368, p. 239 , ISBN 0-7680-0393-8 J Heeter, Precipitation Testing on Large Transport Airplanes, International Conference of Lig
33、htning and Static Electricity. ICOLSE 2005, Lightning and Static Charge Association, September 2005, PST50 P-static Protection for Jet Aircraft / A Summary”, Granger Associates Report, November 1968, (Adapted from the work of J. E. Nanevicz) R. J. Brun and R.G. Dorsch, ”Impingement of Water Droplets
34、 on an Ellipsoid with Fineness Ratio 10 in Axisymmetric Flow”, NACA Technical Note 3147, May 1954 2.5 Definitions and Acronyms 2.5.1 Definitions P-STATIC: P-Static is the process of charging the aircraft with precipitation particles. It results in static electrification of the airframe by frictional
35、 charging of the precipitation particles. During triboelectric charging, the potential of an aircraft increases until a threshold is reached where electrical discharges occur. These electrical discharges generate electromagnetic noise that may interfere with both navigation and communications. Other
36、 sources that can create discharge conditions include, engine exhaust non-neutrality (at low altitudes), and exogenous electric fields (between oppositely charged cloud regions). ARCING: An electrical discharge between surfaces at different potentials. The discharge can produce broadband noise exten
37、ding through 1,000 MHz. ELECTRICAL BOND: An electrical connection between conductive surfaces that allows charge to flow without disruption. CORONA: A luminous discharge that occurs as a result of an electrical potential difference between the aircraft and the surrounding atmosphere. This occurs whe
38、n the aircraft potential increases above the ionizing threshold of aircraft areas with small radius of curvature such as the wing tips, vertical and horizontal stabilizers and blade antennas. CROSS CHARGING: Asymmetric charging of the aircraft due to the aircraft being in an external electric field.
39、 Cross charging is often referred to as exogenous charging. SAE INTERNATIONAL ARP5672 4 OF 29GROUND: An electrical connection to the main airframe STREAMERING: The branch-like ionized paths that occur as a transition phase after a corona regime. Streamers occur for instance across insulating dielect
40、ric surfaces to the metal airframe. This noise source is generated over dielectric surfaces such as radomes, fiberglass winglets and other fiberglass panels positioned on frontal impact areas of the aircraft, if not properly treated. As particles strike, they deposit charges, positive or negative, o
41、n the dielectric surface. The charge density increases until the electric field reaches the ionization threshold point producing coronas and streamers which generates broadband radio noise. TRIBOELECTRIC CHARGING: The generation of static electricity that results from two materials coming into conta
42、ct with sufficient velocity that one of the materials comes away with a positive charge; the other receives a negative charge. Tribo comes from the Latin word meaning “to rub.“ INSTRUMENT METEOROLOGICAL CONDITIONS: Weather conditions below the minimums prescribed for flight under Visual Flight Rules
43、 (VFR). 2.5.2 Acronyms AC Advisory Circular AMM Aircraft Maintenance Manual AM Amplitude Modulated ADF Automatic Direction Finder (radio) AGL Above Ground Level AOA Angle Of Attack CDL Configuration Deviation List CFR Code of Federal Regulations CMM Component Maintenance Manual EASA European Aviatio
44、n Safety Agency EMI Electromagnetic Interference FAA Federal Aviation Administration HF High Frequency (radio) HV High Voltage HVPS High Voltage Power Supply IFR Instrument Flight Rules ILS Instrument Landing System MSL Mean Sea Level OEM Original Equipment Manufacturer RF Radio Frequency SAE Societ
45、y of Automotive Engineers VFR Visual Flight Rules VHF Very High Frequency (radio) VOR VHF Omnidirectional Range SAE INTERNATIONAL ARP5672 5 OF 293. BACKGROUND P-static is the term used to describe electrostatic or triboelectric charging of aircraft surfaces that collide with dust, ice crystals, rain
46、, sand, smoke, snow and other particles during flight. Contact with these particles transfers charge at the point of impact on the aircraft exterior surface, which results in an electrostatic charge accumulation on the aircraft 2.4. The charge accumulation, if not properly managed, will continue to
47、develop on aircraft exterior surfaces until an electrostatic discharge occurs by high voltage corona typically at the enhanced electric field locations at the extremities of the aircraft. Also, if untreated surfaces are exposed to precipitation impingement streamering across dielectric surfaces and
48、discharging of unbonded metal surfaces may occur. These discharges consist of extremely short pulses. These short pulses with fast rise times radiate radio frequency energy, which may have spectral content that extends into the hundreds of megahertz. . When aircraft radio receivers receive the energ
49、y from these pulses, the noise-like signals can be strong enough to interfere with the radio receivers and other sensitive electronics. The result can be loss of, or interference with, the communication, navigation or surveillance functions performed by the radios or other aircraft electronics. 4. P-STATIC PROTECTION DESIGN AND COMPLIANCE The following six activities are elements of an iterative process for design and verification
