1、Designation: F3338 18Standard Specification forDesign of Electric Propulsion Units for General AviationAircraft1This standard is issued under the fixed designation F3338; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of
2、last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification covers minimum requirements for thedesign of Electric Propulsion Units (EPU).1.2 Distributed propul
3、sion is not excluded; however, addi-tional requirements will be needed to address the additionalissues that distributed propulsion can create. Some of thoseissues may include: use of a common motor controller/inverter,segregated electric harnesses, cooling systems, electric powersupplies, and others
4、.1.3 This specification does not address all of the require-ments that may be necessary for possible hybrid configurationswhere an EPU and a combustion engine drive a commonthruster. This specification may be used for the EPU aspectswith supplemental requirements for the thruster and the com-bustion
5、 engine.1.4 This specification does not include the requirements forEPUs that include gearboxes, thrusters, liquid cooling/lubrication, or any energy storage systems. This specificationmay be used for the EPU base aspects with supplementalrequirements for these additional features. This version of t
6、hisASTM specification also does not address all of the require-ments necessary for configurations of motor driven ducted-fans. It is anticipated that the fan would be subject to parts of14 CFR 33 or CS-E and/or 14 CFR 35 or CS-P, or equivalent,in particular blade-off and bird strike. These would be
7、con-ducted on the fan as a unit (including motor) rather than onmotor or fan alone.1.5 The applicant for a design approval shall seek theindividual guidance of their respective civil aviation authority(CAA) body concerning the use of this specification as part ofa certification plan. For information
8、 on which CAA regulatorybodies have accepted this specification (in whole or in part) asa means of compliance to their general aviation aircraftairworthiness regulations (hereinafter referred to as “theRules”), refer to ASTM Committee F39 webpage(www.ASTM.org/COMITTEE/F39.htm), which includes CAAweb
9、site links.1.6 When applicable, this specification may be used forEPUs with a fixed-pitch propeller or fan. These configurationsmay be type-certificated as an EPU including a thruster. Theremay be additional requirements not currently included in thisspecification for this type configuration. In add
10、ition, 5.24 isincluded as a test requirement for the EPU. That sectionrecognizes that the EPU may not have an integral thruster butit must be tested with a representative load on the drive shaftto assure EPU ability to operate properly with static anddynamic loads.1.7 The values stated in inch-pound
11、 units are to be regardedas standard. The values given in parentheses are mathematicalconversions to SI units that are provided for information onlyand are not considered standard.1.8 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is therespo
12、nsibility of the user of this standard to establish appro-priate safety, health, and environmental practices and deter-mine the applicability of regulatory limitations prior to use.1.9 This international standard was developed in accor-dance with internationally recognized principles on standard-iza
13、tion established in the Decision on Principles for theDevelopment of International Standards, Guides and Recom-mendations issued by the World Trade Organization TechnicalBarriers to Trade (TBT) Committee.2. Referenced Documents2.1 Code of Federal Regulations:214 CFR 33 Airworthiness Standards: Aircr
14、aft Engines14 CFR 35 Airworthiness Standards: Propellers2.2 EASA Standards:3CS-E EnginesCS-P Propellers1This specification is under the jurisdiction ofASTM Committee F39 on AircraftSystems and is the direct responsibility of Subcommittee F39.05 on Design,Alteration, and Certification of Electric Pro
15、pulsion Systems.Current edition approved Dec. 1, 2018. Published December 2018. DOI:10.1520/F333818.2Available from U.S. Government Publishing Office (GPO), 732 N. Capitol St.,NW, Washington, DC 20401, http:/www.gpo.gov.3Available from European Aviation Safety Agency (EASA), Postfach 10 12 53,D-5045
16、2 Cologne, Germany, http:/www.easa.europa.eu.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United StatesThis international standard was developed in accordance with internationally recognized principles on standardization established in the Decis
17、ion on Principles for theDevelopment of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.12.3 IEC Standards:4IEC 60034-1 Rotating electrical machines Part 1 Ratingand performanceIEC 60349-4 Electric traction Rotati
18、ng electric machinesfor rail and road vehicles Part 4: Permanent magnetsynchronous electrical machines connected to an elec-tronic converter3. Terminology3.1 Definitions:3.1.1 duty types, n3.1.1.1 non-periodic duty, nin which generally load andspeed vary within the permissible operating range.3.1.1.
19、2 periodic duty, ncomprising one or more loadsremaining constant for the duration specified.3.1.2 electronic controllers, nencompasses inverters.3.1.3 hazardous EPU effects, nthe following effects willbe regarded as Hazardous EPU Effects:(1) Non-containment of high-energy debris;(2) Significant powe
20、r in the opposite direction to thatcommanded by the pilot;(3) Uncontrolled fire;(4) Failure of the EPU mount system leading to inadvertentEPU separation;(5) Release of the propeller or fan or any major portion ofthe propeller or fan by the EPU, if applicable;(6) Complete inability to shut the EPU do
21、wn; and(7) Electrocution of crew or passengers sufficient to causeserious or fatal injury.3.1.4 motor, na machine that converts electrical powerinto rotational mechanical power.3.1.5 motor controller, na device or devices that serves togovern the operation of an electric motor.3.1.5.1 DiscussionIt c
22、ould include a manual or automaticmeans for powering on or stopping the motor, selectingdirection of rotation, selecting and regulating motor speeds,regulating or limiting the torque, and protecting against over-loads and faults. The inverter function is often a part of themotor controller.3.1.6 pow
23、ering on, venergizing, or turning on, the EPU toa ready state such that throttle input results in shaft rotation.3.1.7 rated maximum continuous power, nwith respect toElectric Propulsion Units, the approved brake horsepower thatis developed statically or in flight, in standard atmosphere at aspecifi
24、ed altitude, within the EPU operating limitations estab-lished under CAA requirements, and approved for unrestrictedperiods of use.3.1.8 rated takeoff power, nwith respect to Electric Pro-pulsion Units type certification, the approved brake horse-power that is developed statically under standard sea
25、 levelconditions, within the EPU operating limitations establishedunder CAA requirements, and limited in use to periods of notover 5 min for takeoff operation.3.1.9 shaft power (or simply power), nthe power deliveredat an EPUs drive shaft.3.1.9.1 DiscussionReferences to electrical power will becalle
26、d out as such.3.2 Definitions of Terms Specific to This Standard:3.2.1 electric propulsion unit (EPU), nin the context ofthis standard, a minimum EPU is comprised of the electricmotor, associated electronic controllers, disconnects, wiring,and sensors.3.2.2 thrust, vas used in this standard, only ap
27、plies toendurance, durability, and systems tests.3.2.3 thruster, nas used in this standard, a device such aspropeller, rotor, or fan for translating mechanical/rotationalenergy to thrust.3.3 Abbreviations:3.3.1 EMIelectromagnetic interference3.3.2 HIRFhigh-intensity radiated field4. Significance and
28、 Use4.1 This specification provides designers and manufacturersof electric propulsion for General Aviation aircraft referencesand criteria to use in designing and developing EPUs with theintent of gaining approval from a civil aviation authority.4.2 Appendix X1 provides additional (but not necessari
29、lyall) information and guidance to meet certification or airwor-thiness requirements, or both, for a particular country or areaunder the jurisdiction of a civil aviation authority.5. Requirements in Support of Certification or Approval5.1 Instructions for Continued Airworthiness:5.1.1 Instructions f
30、or continued airworthiness must be pre-pared. The instructions may be incomplete at the time ofcertification or approval:5.1.1.1 If a program exists to ensure their completion priorto delivery of the first aircraft with the EPU installed, or5.1.1.2 Upon CAA approval for the aircraft with the EPUinst
31、alled, whichever occurs later.5.1.2 A maintenance manual shall be provided that definesmaintenance requirements for the continued airworthiness ofthe EPU, such as periodic installed maintenance, majorinspections, repairs, replacement or overhaul intervals, and anyother maintenance limitations includ
32、ing limited life compo-nents requiring replacement between overhaul intervals. Main-tenance requirements for the continued airworthiness of theEPU also includes special equipment or testing required toensure the electrical propulsion system is safe to continuedoperation.5.1.3 If applicable, an overh
33、aul manual that provides in-structions for disassembling, replacing, or overhauling compo-nents identified in the manual for such, in order to return theEPU to airworthy condition that is safe for operation until thenext major overhaul.5.1.4 Updates to the Instructions for Continued Airworthi-ness m
34、ust be made available by the EPU manufacturer or otherresponsible party such that those instructions remain current.4Available from International Electrotechnical Commission (IEC), 3, rue deVaremb, 1st Floor, P.O. Box 131, CH-1211, Geneva 20, Switzerland, http:/www.iec.ch.F3338 1825.2 Instruction Ma
35、nual for Installing and Operating theEPU:5.2.1 Instructions for installing and operating the EPU mustbe made available to the CAA as part of the certificationprocess and to the customer at the time of delivery of the EPU.The instructions must include directly, or by reference toappropriate documenta
36、tion, at least the following:5.2.1.1 Installation InstructionsCoordination is recom-mended between the EPU manufacturer and the installer.However, if the installer is not identified at the time of EPUdesign, the following aspects still need definition in theinstallation instructions.(1) An outline d
37、rawing of the EPU including overalldimensions.(2) A definition of the physical and functional interfaces ofall elements of the EPU, with the aircraft and aircraftequipment, including the propeller or fan, when applicable.Including the location and description of EPU connections forattachment of acce
38、ssories, wires, cables, cooling ducts,cowling, and any other equipment attached to the EPU.(3) Where an EPU system relies on components that arenot part of the EPU type design, the interface conditions andreliability requirements for those components, as used in thesafety analysis, must be specified
39、 in the EPU installationinstructions. If reliability values used in the safety analysis arebased on assumptions, these assumed values must be specifiedin the EPU installation instructions. Requirements for mitiga-tion means, that are not part of the EPU, must be specified inthe installation and oper
40、ation instructions.(4) A list of the instruments necessary for the control andoperation of the EPU, including the overall limits of accuracyand transient response requirements, must be stated in amanner that allows the satisfactory nature of instruments asinstalled to be determined.NOTE 1“Instrument
41、” is used to refer to any device necessary tomeasure EPU parameters and convey them to the appropriate decision-making center, be that a pilot or software-based control.(5) The limits on environmental conditions, including EMI,HIRF, and lightning for which the EPU was designed andqualified.5.2.1.2 O
42、peration Instructions:(1) The operating limitations established within the show-ing of compliance.(2) The power ratings and procedures for correcting fornonstandard atmosphere.(3) The recommended procedures, under normal and criti-cal ambient conditions for:(a) Powering on;(b) Operating on the groun
43、d;(c) Operating during flight.(4) A description of the primary and all alternate modes,and any back-up system, together with any associatedlimitations, of the EPU control system and its interface with theaircraft systems, including the propeller or fan if these areintegral with the EPU.5.3 EPU Opera
44、ting Limitations and Ratings:5.3.1 Ratings and operating limitations are established bythe administrator and included in the product certificate datasheet, including ratings and limitations based on the operatingconditions and information specified in this section, asapplicable, and any other inform
45、ation found necessary for safeoperation of the engine.5.3.2 EPU operating limitations are established asapplicable, including:5.3.2.1 Maximum transient rotor shaft overspeed and time;5.3.2.2 Maximum transient EPU overtorque and time, andnumber of overtorque occurrences;5.3.2.3 Maximum EPU overtorque
46、 and time;5.3.2.4 Electrical power, voltage, current, frequency, andelectrical power quality limits;5.3.2.5 Maximum rated temperature;5.3.2.6 Maximum and minimum continuous temperature,current, voltage;5.3.2.7 Vibration limits; and5.3.2.8 Any other information necessary for safe operationof the EPU.
47、5.3.3 EPU ratings are established, as applicable, and arebased on the intended duty cycle and the assignment of ratingsas defined below, including:5.3.3.1 Power, torque, speed, and time for:(1) Rated maximum continuous power, and(2) Rated maximum temporary power and associated timelimit.5.3.4 Duty C
48、ycle:5.3.4.1 Declaration of DutyThe intended duty cycle of theEPU sets the framework for establishment of the ratings. Thereare a number of typical duty cycles used for electric motors.(See IEC 60034-1.) As the duty cycle combined with the ratingat that duty cycle establishes the capability and the
49、limits forthe EPU use, the manufacturer declares the duty cycle orcycles. These can be based on the manufacturers intended usefor the EPU or may be based on the required duty cycle of theinstaller. As detailed in IEC 60034-1, multiple duties and theirassociated ratings may be established to address variousoperational conditions. The duty may be described by one ofthe following:(1) Numerically, where the load does not vary or where itvaries in a known manner; or(2) As a time sequence graph of the variable quantities; or(3) By selecting one of the typical
