1、Designation: F3239 18Standard Specification forAircraft Electric Propulsion Systems1This standard is issued under the fixed designation F3239; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number in p
2、arentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification addresses airworthiness requirementsfor the design and installation of electric propulsion systemsfor aeroplanes. Hybrid-electr
3、ic propulsion systems are ad-dressed implicitly unless explicitly stated otherwise. Thisspecification was written with the focus on electric propulsionsystems with conventional system layout, propulsioncharacteristics, and operation. The content may be morebroadly applicable; it is the responsibilit
4、y of the applicant tosubstantiate broader applicability as a specific means of com-pliance.1.2 An applicant intending to propose this information asMeans of Compliance for a design approval must seek guid-ance from their respective oversight authority (for example,published guidance from applicable
5、CAAs) concerning theacceptable use and application thereof. For information onwhich oversight authorities have accepted this standard (inwhole or in part) as an acceptable Means of Compliance totheir regulatory requirements (hereinafter “the Rules”), refer tothe ASTM Committee F44 web page (www.astm
6、.org/COMMITTEE/F44.htm).1.3 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety, health, and environmental practices and deter-mine the applicability of regulatory
7、limitations prior to use.1.4 This international standard was developed in accor-dance with internationally recognized principles on standard-ization established in the Decision on Principles for theDevelopment of International Standards, Guides and Recom-mendations issued by the World Trade Organiza
8、tion TechnicalBarriers to Trade (TBT) Committee.2. Referenced Documents2.1 ASTM Standards:2F3060 Terminology for AircraftF3061/F3061M Specification for Systems and Equipment inSmall AircraftF3062/F3062M Specification for Aircraft Powerplant Instal-lationF3063/F3063M Specification for Aircraft Fuel a
9、nd EnergyStorage and DeliveryF3064/F3064M Specification for Aircraft PowerplantControl, Operation, and IndicationF3065/F3065M Specification for Aircraft Propeller SystemInstallationF3066/F3066M Specification for Aircraft Powerplant Instal-lation Hazard MitigationF3114/F3114M Specification for Struct
10、uresF3116/F3116M Specification for Design Loads and Condi-tionsF3120/F3120M Specification for Ice Protection for GeneralAviation AircraftF3316/F3316M Specification for Electrical Systems for Air-craft with Electric or Hybrid-Electric Propulsion2.2 FAA Standards:3AC23-16 Systems and Equipment Guide f
11、or Certification ofPart 23 Airplanes and Airships3. Terminology3.1 The following is a selection of relevant terms. SeeTerminology F3060 for more definitions and abbreviations.3.2 Definitions:3.2.1 capacitytotal amount between minimum and maxi-mum condition (for example, empty and full).1This specifi
12、cation is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.40 onPowerplant.Current edition approved Sept. 1, 2018. Published September 2018. DOI:10.1520/F3239-18.2For referenced ASTM standards, visit the ASTM website, www.as
13、tm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.3Available from Federal Aviation Administration (FAA), 800 IndependenceAve., SW, Washington, DC 20591, http:/www.faa.gov.Co
14、pyright 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 Decision on Principles for theDevelopment of Interna
15、tional Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.13.2.2 electric propulsion unit (EPU)the EPU shall as aminimum consist of the electric motor, associated electroniccontrollers, disconnects, wiring, and monitoring gauges a
16、ndmeters.3.2.2.1 DiscussionThe EPU is an aircraft engine.3.2.3 energy distribution systema system that providesenergy for propulsion from the energy storage systems to thepropulsive units.3.2.3.1 DiscussionThe energy distribution system is con-sidered equivalent to the fuel system on liquid hydrocar
17、bonbased powerplants.3.2.4 energy storage system (ESS)a source (component orsystem) that stores and provides energy that can be drawn uponfor propulsion.3.2.4.1 DiscussionTypical energy storage systems includebut are not limited to batteries, fuel cell systems or capacitorsand their integrated manag
18、ement systems, if installed. Theenergy storage system is considered equivalent to a fuel tankon liquid hydrocarbon based powerplants.3.2.5 quantityamount available at the time of measure-ment.3.2.6 usable energy capacityminimum capacity of anenergy storage system between the defined fully charged an
19、dthe minimum charge state which can be drawn upon at any rateup to maximum rated power of this energy storage systemunder any likely operating condition.4. Powerplant Installation4.1 General:4.1.1 Each powerplant installation shall meet the applicablerequirements of Specification F3062/F3062M.4.1.2
20、Each propeller system shall meet the applicable re-quirements of Specification F3065/F3065M.4.1.3 Each EPU shall meet the technical requirements of anaccepted specification appropriate to the application.5. Energy Distribution Systems5.1 General:5.1.1 Each energy distribution system shall meet the a
21、ppli-cable requirements of Specification F3063/F3063M andF3316/F3316M.5.1.2 Each energy distribution system shall safely providesufficient power to each EPU under the most critical operatingconditions.5.1.3 The combined usable energy capacity of all energystorage systems shall be enough to maintain
22、maximum con-tinuous power of the EPU for a minimum of 30 minutes. Forhybrid systems this may be accomplished with any combina-tion of generation and energy storage.NOTE 1Operational rules for which the aeroplane is intended to beused may require greater endurance.5.2 Independence:5.2.1 For aeroplane
23、s with multiple EPUs, the energy distri-bution system shall be designed so that, in at least one systemconfiguration, the failure of any one component will not resultin the loss of power of more than one EPU or requireimmediate action by the pilot to prevent the loss of power ofmore than one EPU.NOT
24、E 2Refer toAC23-16 for guidance on the independence of energydistribution systems.5.3 Energy Storage System:5.3.1 General:5.3.1.1 Each energy storage system shall meet the require-ments of an accepted specification appropriate to the applica-tion.5.3.1.2 Each energy storage system shall be installed
25、 inaccordance with the applicable installation instructions.5.3.1.3 Each energy storage system shall be designed tosafely deliver the required power under the conditions specifiedin 5.1.2 when drawn upon.5.3.2 Installation:5.3.2.1 Each energy storage system shall be supported towithstand the vibrati
26、on and inertia loads to which it may besubjected in operation.5.3.2.2 Each energy storage system shall have access pro-visions for maintenance.5.3.2.3 Design precautions shall be taken to minimize thehazards to the aircraft in the event of a fire or sudden dischargewhich could result in damage to co
27、mponents, structure, orflight controls near the storage area.5.3.2.4 The energy storage system installation shall protectthe occupants and the critical airframe and systems from asingle cell thermal runaway.5.3.3 Compartments:5.3.3.1 Each energy storage system shall be ventilated anddrained as neces
28、sary to prevent accumulation of hazardous,flammable, or corrosive fluids or vapors.5.3.3.2 Each energy storage system shall be isolated frompersonnel compartments by an enclosure that is vented anddrained to the exterior of the aeroplane.5.3.3.3 Any enclosure required by 5.3.3.2 shall sustain anyper
29、sonnel compartment pressurization loads without perma-nent deformation or failure under the conditions defined inSpecifications F3116/F3116M and F3114/F3114M.5.3.3.4 For energy storage systems in compartments adja-cent to fire zones there shall be sufficient clearance or insula-tion between the comp
30、artment and the firewall to preventignition or malfunction of the energy storage system as a resultof fire in the fire zone.5.3.4 Energy Capacity:5.3.4.1 The usable energy capacity for each energy storagesystem shall be established.5.3.4.2 The available remaining energy quantity informa-tion shall b
31、e provided.5.3.5 Charging System:5.3.5.1 The charging connection and system shall be de-signed to minimize hazards to personnel.5.3.5.2 The charging connection shall be designed to ensurecorrect connection of the charging connector.5.3.5.3 The charging system shall be designed to protect theaeroplan
32、e from a charging source with incorrect voltageincluding high voltage, low voltage, incorrect polarity, effectsof shorting, and type of current (AC/DC).F3239 1825.3.6 Pilot-replaceable Energy Storage Systems:5.3.6.1 Each energy storage system location where electri-cal components can be replaced sha
33、ll be marked.5.3.6.2 Design precautions shall be taken to prevent incor-rect installation of components when replaced in operation.6. Control and Indication6.1 General:6.1.1 Each powerplant installation shall meet the applicablerequirements of Specification F3064/F3064M.6.1.2 For any energy storage
34、system that should not bedepleted in normal operation, there shall be a separate indica-tion to the flight crew when less than approximately 30 minutesof usable energy quantity or 50 % of the usable energy capacityremains in the energy storage system, whichever is less.6.2 Controls:6.2.1 There shall
35、 be a means to provide separate powercontrol for each EPU, unless it can be shown that multipleEPUs operated by a single control will not prevent the isolationof a failed unit, and the control of the remaining units to ensurecontinued, safe flight and landing.6.2.2 Shutoff Controls:6.2.2.1 There sha
36、ll be an independent, simple, and reliablemeans to disconnect each energy storage system.6.2.2.2 If the EPU or energy storage system is installed in afire zone, there shall be a means to allow appropriate flightcrew members to rapidly shut off, in flight, the energy supplyto the EPUs and energy stor
37、age system individually.6.2.2.3 No shutoff means may be on the fire zone side of anyfirewall.6.2.2.4 There shall be a means to guard against inadvertentoperation of each shutoff means.6.2.2.5 There shall be a means to allow appropriate flightcrew members to reopen the shutoff means rapidly after it
38、hasbeen closed.6.3 Powerplant Operational Characteristics and Installa-tion:6.3.1 General:6.3.1.1 Electric propulsion systems shall have no adversecharacteristics during normal or emergency operation withinthe operating limitations. This investigation shall consider theresults of inadvertent energy
39、storage system overcharging orlimited energy dumping capability, or both, during propellerwindmilling and reversing operation.6.3.2 Cooling Test Requirements:6.3.2.1 For showing compliance with the general coolingrequirements of Specification F3064/F3064M the aeroplaneshall be flown in the configura
40、tions, at the speeds, andfollowing the procedures recommended in theAeroplane FlightManual that correspond to the applicable performance require-ments that are critical to cooling.6.3.3 Starting and Stopping:6.3.3.1 The design of the installation shall be such that riskof fire or mechanical damage t
41、o the EPU or the aeroplane,because of starting the EPU in any conditions in which startingis to be permitted, is reduced to a minimum. Any techniquesand associated limitations shall be established and included inthe Aeroplane Flight Manual, approved manual material, orapplicable operating placards.6
42、.3.3.2 There shall be a means for stopping the rotation ofany EPU or component, if continued rotation would cause ahazard to the aeroplane.6.3.3.3 If hydraulic propeller feathering systems are usedfor stopping the EPU, the hydraulic feathering lines or hosesshall be fire resistant under the operatin
43、g conditions expectedduring feathering.6.3.3.4 Restart EnvelopeAn altitude and airspeed enve-lope shall be established for the aeroplane for inflight enginerestarting and each installed EPU shall have a restart capabilitywithin that envelope.6.3.3.5 Restart CapabilityNo unsafe condition may arisefro
44、m re-engaging any EPU after a shutdown either on groundor in flight.6.3.4 Powerplant Limitations:6.3.4.1 The powerplant limitations shall be established sothat they do not exceed the corresponding limits of the EPUs,the energy storage systems and associated equipment.7. Hazard Mitigation7.1 General:
45、7.1.1 Each powerplant installation shall meet the applicablerequirements of Specification F3066/F3066M.7.1.1.1 For compliance with the engine isolation require-ments of Specification F3066/F3066M “an energy storagesystem, if only one energy storage system is installed” isconsidered “a fuel tank, if
46、only one fuel tank is installed.”7.2 High Energy Rotors:7.2.1 Each high energy rotor shall meet the applicablerequirements for high energy rotors of Specification F3061/F3061M.NOTE 3Depending on the specific design, electric motors may qualifyas high energy rotors.7.3 Fire Protection:7.3.1 Designate
47、d Fire Zones:7.3.1.1 The EPU or ESS section is a designated fire zone, ifa fire hazard exists.7.3.2 Fire Detection:7.3.2.1 There shall be means that ensure the prompt detec-tion of a fire in each fire zone that is not visible to the crew.7.3.3 Lightning Protection:7.3.3.1 For level 1 aircraft intend
48、ed for night VFR and IFRoperation and for level 2 or higher aircraft, each energy storagesystem shall be designed and arranged to prevent the ignitionof flammable vapor or contents within the system by corona orstreamering at vent outlets and ESS areas.7.4 Ice Protection:7.4.1 Each air inlet of the
49、powerplant installation shall beprotected from ice accumulation, when operated in the condi-tions for which it is to be certified as defined in SpecificationF3120/F3120M.8. Keywords8.1 electric aircraft; electric propulsion; EPU; ESS; power-plantF3239 183ASTM International takes no position respecting the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent rights, and the riskof infringement of such rights, are entirely their own
