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 entirelyvoluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefro
2、m, 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 2011 SAE InternationalAll rights reserved. No part of this publication may be
3、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)Fax: 724
4、-776-0790Email: custsvcsae.orgSAE WEB ADDRESS: http:/www.sae.orgAEROSPACE RECOMMENDEDPRACTICEARP5015REV.AIssued 1996-06Revised 2003-04Superseding ARP5015Ground Equipment - 400 Hertz Ground Power Performance RequirementsTABLE OF CONTENTS1. SCOPE .22. APPLICABLE DOCUMENTS22.1 SAE Publications .22.2 AN
5、SI Publications 32.3 U.S. Government Publications.32.4 UL Publications32.5 NEMA Publications 32.6 IEC Publications 32.7 ATA Publications32.8 Other Publications .42.9 Definitions and Abbreviations 43. TECHNICAL REQUIREMENTS .73.1 Equipment Specifications 73.2 Personnel Safety .103.3 Equipment Protect
6、ion 113.4 Interface Requirements123.5 Tools and Test Equipment123.6 Design and Construction .124. INSTALLATION OPERATION AND MAINTENANCE.155. NOTES .15FIGURE 1 Voltage Compliance and Protection 9FIGURE 2 Frequency Compliance and Protection . 11SAE values your input. To provide feedback on this Techn
7、ical Report, please visit http:/www.sae.org/technical/standards/ARP5015AReaffirmed 2011-01SAE ARP5015 Revision A- 2 -1. SCOPE:1.1 This SAE Aerospace Recommended Practice (ARP) covers the requirements for ground power equipment that supplies 115/200 V, 3-phase, 400 Hz output capable of powering aircr
8、aft type loads requiring MIL-STD-704E/DFS-400 quality power. All forms of ground power including mobile and fixed systems are addressed by this document. High voltage (270 V DC) systems are not included in this specification.1.2 The intent of this document is to provide specifications for engine gen
9、erators, motor generators, and solid-state converters tailored for performance with modern aircraft, applicable to all unless otherwise noted. Modern aircraft are requiring more power at a higher quality without interruption which places new constraints such as No-Break-Power-Transfer (NBPT) operati
10、on on the ground power units (GPUs). The protective trip limits are designed to allow a two tier protection utilizing both the aircrafts electrical power generating systems (EPGS) and the GPUs protection. Some of these specifications will place some new design constraints on the manufacturers of GPU
11、s but will help promote compatibility with old and new aircraft with all types of ground power equipment.1.3 While GPUs are designed to provide the same quality of power as the aircrafts EPGS, there are differences in rated capacity. Engines utilized in GPUs must be sized for the peak kW specified w
12、hich is why a 125% overload is specified for GPUs. Increasing the size of the engine to match the aircrafts EPGS typical 150 to 200% overload rating would not be practical. The 150 to 200% overload rating is designed for abnormal conditions (such as fault clearing) and the use of a GPU to clear airc
13、raft on-board faults is not recommended. GPUs that utilized engine generators are also self-excited which implies that they are not capable of providing output under excessive fault current since their output voltage is utilized to excite the generator. Most aircraft EPGS have a permanent magnet pil
14、ot machine that provides the excitation supply to allow for fault clearing current. GPUs are typically rated for a 0.8 power factor which differs from aircraft EPGS which are rated at 0.75 PF. An engine generator will have to have slightly larger engine to accommodate a 0.8 PF when compared to a 0.7
15、5 PF which infers that 0.8 is actually a conservative rating for GPUs.2. APPLICABLE DOCUMENTS:The following publications 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 eff
16、ect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.2.1 S
17、AE Publications:Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001.ARP1247A General Requirements for Aerospace Powered Mobile GroundJ1175 Bystander Sound Level Measurement ProcedureSAE ARP5015 Revision A- 3 -2.2 ANSI Publications:Available from ANSI, 25 West 43rd Street, New York,
18、 NY 10036-8002.ISO 1540 Aerospace - Characteristics for Aircraft Electrical SystemsISO 6858 Ground Support Electrical Supplies - General Requirements2.3 U.S. Government Publications:Available from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.MIL-G-
19、21480A Generators and Regulators, Air-cooled, AC, EquipmentMIL-STD-461 Electromagnetic Interface Characteristic Requirements for EquipmentMIL-STD-704E Electric Power, Aircraft, Characteristics and Utilization of 2.4 UL Publications:Available from Underwriter Laboratories Publications, 333 Pfingsten
20、Road, Northbrook, IL 60062.UL 1446-1980 Systems of Insulating Materials - General Revised 3/862.5 NEMA Publications:Available from National Electrical Manufacturers Association, 2101 L Street, NW, Washington, DC 20037.NEMA MG-1 NEMA Standards Publication - Motor and Generators (N/A to Solid-State)NE
21、MA PE-1 Uninterruptable Power Systems2.6 IEC Publications:Available from International Electrotechnical Commission, 3. rue de Varembe. CH-1211 Geneve 20 Switzerland.IEEE-519 Guide for Harmonic Control and Reactive Compensation of Static Converters2.7 ATA Publications:Available from Air Transport Ass
22、ociation, 1709 New York Avenue NW, Washington, DC 20006ATA-Spec 101 Specification for Ground Power Equipment Technical DataSAE ARP5015 Revision A- 4 -2.8 Other Publications:AN-3114, AN-3440 Army/Navy 6-Pole Socket/Plug Reqmts. (MS90362-MS25486 Cable:MS90328)BSI 2G-219 General Requirements for Ground
23、 Support Electrical Supplies for AircraftDFS-400 Eurostandard 400 Hertz Systems2.9 Definitions and Abbreviations:This glossary of terms is included as part of this document for use in its interpretation.ADJUSTABLE VOLTAGE RANGE: The range in adjustment as controlled by the regulator to enable checki
24、ng over and under voltage protection devices.ALTERNATOR SPEED: The nominal speed at which the alternator operates to produce 400 Hz.ALTITUDE: The maximum height in feet above sea level at which the unit must operate and maintain characteristics within recommended limits.AMBIENT TEMPERATURE RATING: T
25、he temperature range in degrees in which the unit must operate and maintain characteristics within recommended limits.BREAK TRANSFER: The mode of transferring the aircraft load from aircraft power source to ground power source or vice versa whereby power to the aircraft is momentarily interrupted.CR
26、EST FACTOR: The ratio of the peak voltage to the rms voltage. The ratio with a true sine wave is 1.414.DEAD FRONT: Constructed so that there are no exposed live parts on the front of the assembly.DIELECTRIC TESTS: The high voltage impressed across the primary and secondary of a transformer and betwe
27、en a component and the chassis of the unit. This test is used to check insulation characteristics.FREQUENCY CHARACTERISTIC OF VOLTAGE MODULATION: The component frequencies which make up the modulation envelope waveform.FREQUENCY DRIFT: The slow and random variation in frequency within the steady sta
28、te limits.FREQUENCY DRIFT RATE: The rate of change of frequency due to frequency drift when plotted against time.FREQUENCY MODULATION: The cyclic variation of instantaneous frequency about a mean frequency during any steady state load. Frequency modulation in percent is calculated by taking maximum
29、frequency minus minimum frequency times 100 and dividing this value by maximum frequency plus minimum frequency.SAE ARP5015 Revision A- 5 -2.9 (Continued):FREQUENCY MODULATION RATE: The rate of change of frequency due to frequency modulation when plotted against time.FREQUENCY REGULATION: The brand
30、that the output frequency stays within except during transients.FREQUENCY TRANSIENT RECOVERY: The time required for the output frequency to recover to and remain within the prescribed limits after load application or removal.FREQUENCY TRANSIENTS: The maximum instantaneous deviation of the output fre
31、quency from the frequency regulation band.HIGHEST PHASE VOLTAGE LIMITING: A means of limiting the highest phase voltage of the unit output during any unbalanced load condition.INDIVIDUAL HARMONIC: The rms value of any individual harmonic voltage when measured with a harmonic analyzer. This value is
32、expressed as a percentage of the fundamental.LINE DROP COMPENSATION: A system of increasing the unit output voltage in proportion to the current and power factor in the output cable(s) such that the voltage is held constant at the aircraft receptacle.NO BREAK POWER TRANSFER (NBPT): The mode of trans
33、ferring the aircraft load from aircraft power source to ground power source or vice versa whereby the aircraft and ground power sources are simultaneously connected to the aircraft load and in parallel with each other, possibly out of synchronization. NBPT can also occur between on-board aircraft so
34、urces as well.NOMINAL VOLTAGE RATING: The root-mean-square line-to-neutral and line-to-line voltage at which the unit output is rated. The unit is normally set such that output voltage is maintained at this value.OUTPUT TERMINALS: The terminal on the ground power unit side of the output power feeder
35、s. This is considered to be the point of regulation for the ground power unit.OVERLOAD RATING: The normal overload value expressed in kVA at 0.8 power factor for specified time.PHASE VOLTAGE BALANCE WITH BALANCED LOAD: The maximum deviation of any of the three phase voltages from the average of the
36、three phase voltages with a balanced three-phase load. The percent unbalance is calculated by taking maximum deviation of any one line-to-neutral voltage from the average of the three phase voltages times 100 divided by the average of the three phase voltages.SAE ARP5015 Revision A- 6 -2.9 (Continue
37、d):PHASE VOLTAGE BALANCE WITH UNBALANCED LOAD: The maximum deviation of any of the three phase voltages from the average of the three phase voltages with a prescribed unbalanced load. Percent unbalance is calculated in the same method as under balanced load conditions.PHASE VOLTAGE DISPLACEMENT WITH
38、 BALANCED LOAD: The maximum deviation in degrees from 120 degrees between phases of the alternator voltages during balanced load conditions.PHASE VOLTAGE DISPLACEMENT WITH UNBALANCED LOAD: The maximum deviation in degrees from 120 degrees between phases of the alternator voltages during a prescribed
39、 unbalanced load.PRIME MOVER: The source of power for driving the alternator.REGULATOR SENSING: The means by which the voltage is sensed and fed to the voltage regulator.REMOTE SENSING: A means of providing constant voltage at the aircraft receptacle(s) by sensing the voltage at the receptacle with
40、three separate leads in the output cable.SHORT-CIRCUIT CURRENT: Aircraft onboard power systems typically provide current limit between 2.2 and 3.0 per unit operator. The voltage is folded back to accomplish this current limit mode. The purpose is to allow shorts to clear and assure operation of the
41、protective current trips on the aircraft power bus. GPUs typically do not provide this mode since it is undesirable to have a GPU feeder fault arc for 5 s prior to tripping. Also, voltage foldback during NBPT is undesirable due to GPU and aircraft power control interactions.TEMPERATURE RISE: The ris
42、e in degrees above ambient for components of the unit.TOTAL HARMONIC CONTENT: The total RMS voltage remaining when the fundamental component is removed. This value is determined by calculating the square root of the sum of the squares of the individual harmonics and expressing this value as a percen
43、tage of the fundamental.TOTAL LIFE: Defined to be the hours of use from time of delivery of the equipment to the using activity until its identity is destroyed by classifying it as salvage and/or subject to cannibalization.TRIP: Occurs when the output is turned off or the output contactor is opened.
44、TYPE OF MOUNTING: The means of mounting the unit and controls.UNIT: Refers to the complete power package such as the prime mover, alternator, and all associated equipment and systems.UNIT RATING: The full load value (rated continuous) expressed in kVA at 0.8 power factor. The unit shall be capable o
45、f operating at any power factor from 0.8 lagging to 1.0 (unity) with reduced output power at higher power factors.SAE ARP5015 Revision A- 7 -2.9 (Continued):VOLTAGE MODULATION: The cyclic variation about an average of the AC peak voltage during any steady state load. The modulation envelope is forme
46、d by a continuous curve connecting each sine wave peak. Voltage modulation in percent is calculated by taking maximum voltage minus minimum voltage times 100 and then dividing this value by maximum voltage plus minimum voltage.VOLTAGE REGULATION: The band that the output voltage stays within except
47、during transients.VOLTAGE REGULATION STEADY STATE: The band that the output voltage stays within with a fixed load.VOLTAGE TRANSIENTS: The maximum momentary deviation of the output voltage from the steady state voltage as a result step load changes.VOLTAGE TRANSIENT RECOVERY: The time required for t
48、he output voltage to recover to and remain within the prescribed limits after load application or removal.3. TECHNICAL REQUIREMENTS:3.1 Equipment Specifications:All specifications are referenced to the units output terminals unless otherwise stated.3.1.1 Output Rating: The engine generator, motor ge
49、nerator, or solid state converter shall be of sufficient capacity to produce the rated kVA at 0.8 power factor and specified overload at the altitude and temperature range in which the equipment will be operated. The unit shall be capable of operating at any power factor from 0.8 lagging to 1.0 (unity) with reduced output power at higher power factors.3.1.2 Alternator Speed: Shall be based on the continuous operating speed of the prime mover. Not applicable to Solid-State.3.1.3 Temperature Rise: Components of an alternator shall have insulating properties meeting NE
