ASTM F2564-2013 Standard Specification for Design and Performance of a Light Sport Glider《轻型运动滑翔机的设计和性能标准规范》.pdf
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1、Designation: F2564 13Standard Specification forDesign and Performance of a Light Sport Glider1This standard is issued under the fixed designation F2564; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A n
2、umber 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 airworthiness requirements forthe design of a powered or non-powered fixed wing light sportaircraft, a “glider
3、.”1.2 This specification is applicable to the design of a lightsport aircraft glider as defined by regulations and limited to dayVFR flight.1.3 A glider for the purposes of this specification is definedas a heavier than air aircraft that remains airborne through thedynamic reaction of the air with a
4、 fixed wing and in which theability to remain aloft in free flight does not depend on thepropulsion from a power plant.Apowered glider is defined forthe purposes of this specification as a glider equipped with apower plant in which the flight characteristics are those of aglider when the power plant
5、 is not in operation.1.4 The values in SI units are to be regarded as the standard.The values in parenthesis are for information only.1.5 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 esta
6、blish appro-priate safety and health practices and determine the applica-bility of regulatory requirements prior to use.2. Referenced Documents2.1 ASTM Standards:2F2279 Practice for Quality Assurance in the Manufacture ofFixed Wing Light Sport AircraftF2295 Practice for Continued Operational Safety
7、Monitor-ing of a Light Sport AircraftF2316 Specification for Airframe Emergency ParachutesF2339 Practice for Design and Manufacture of Reciprocat-ing Spark Ignition Engines for Light Sport AircraftF2840 Practice for Design and Manufacture of ElectricPropulsion Units for Light Sport Aircraft2.2 Other
8、 Standards:CS-22 Subpart H Certification Specifications for Sailplanesand Powered Sailplanes33. Terminology3.1 Definitions:3.1.1 electric propulsion unit, EPUany electric motor andall associated devices used to provide thrust for an electricaircraft.3.1.2 energy storage device, ESDused to store ener
9、gy aspart of a Electric Propulsion Unit (EPU). Typical energystorage devices include but are not limited to batteries, fuelcells or capacitors.3.1.3 featheringa single action from the cockpit thatrepositions the propeller blades to low drag configuration whenthe engine is not operating.3.1.4 flapsan
10、y movable high lift device.3.1.5 maximum empty weight, WE(kg) largest emptyweight of the glider, including all operational equipment that isinstalled in the glider: weight of the airframe, powerplant,excluding energy storage device (ESD) for electric propulsionunit when removable, required equipment
11、, optional and spe-cific equipment, fixed ballast, full engine coolant and oil,hydraulic fluid, and the unusable fuel. Hence, the maximumempty weight equals maximum takeoff weight minus minimumuseful load: WE= W WU.3.1.6 minimum useful load, WU(kg) where WU= W WE.3.1.7 The terms “engine” referring t
12、o internal combustionengines and “motor” referring to electric motors for propulsionare used interchangeably within this standard.3.1.8 The term “engine idle” or “throttle closed” when inreference to electric propulsion units shall mean the minimumpower or propeller rotational speed condition for th
13、e electricmotor as defined without electronic braking of the propellerrotational speed.3.2 Abbreviations:3.2.1 AOIAircraft Operating Instructions3.2.2 ARAspect Ratio = b2/S1This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the direct responsibility of S
14、ubcommittee F37.10 on Glider.Current edition approved May 1, 2013. Published June 2013. Originallyapproved in 2006. Last previous edition approved in 2011 as F2564 11. DOI:10.1520/F2564-13.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at servic
15、eastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.3Available from European Aviation Safety Agency (EASA), Postfach 10 12 53,D-50452 Koeln, Germany, http:/www.easa.eu.int/home.php.Copyright ASTM International, 100 Barr Harb
16、or Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States13.2.3 bwing span (m)3.2.4 cchord (m)3.2.5 CAScalibrated air speed (m/s, kts)3.2.6 CLlift coefficient of the aircraft3.2.7 CDdrag coefficient of the aircraft3.2.8 CGcenter of gravity3.2.9 Cmmoment coefficient (Cmis with respect to
17、 c/4point, positive nose up)3.2.10 CMOzero lift moment coefficient3.2.11 Cnnormal coefficient3.2.12 gacceleration as a result of gravity = 9.81 m/s23.2.13 IASindicated air speed (m/s, kts)3.2.14 ICAOInternational Civil Aviation Organization3.2.15 LSAlight sport aircraft3.2.16 nload factor3.2.17 n1gl
18、ider positive maneuvering limit load factorat VA3.2.18 n2glider positive maneuvering limit load factorat VD3.2.19 n3glider negative maneuvering limit load factorat VA3.2.20 n4glider negative maneuvering limit load factorat VD3.2.21 qdynamic pressure = 0.004823 V2kg/m2, when Vis in km/h3.2.22 Swing a
19、rea (m2)3.2.23 Vairspeed (m/s, kts)3.2.24 VAdesign maneuvering speed3.2.25 VCdesign cruising speed3.2.26 VDdesign diving speed3.2.27 VDFdemonstrated flight diving speed3.2.28 VFdesign flap speed3.2.29 VFEmaximum flap extended speed3.2.30 VHmaximum speed in level flight with maximumcontinuous power (
20、corrected for sea level standard conditions)3.2.31 VLOmaximum speed for landing gear extended3.2.32 VNEnever exceed speed3.2.33 VSstalling speed or minimum steady flight speed atwhich the aircraft is controllable (flaps retracted)3.2.34 VS1stalling speed, or minimum steady flight speedin a specific
21、configuration3.2.35 VS0stalling speed or minimum steady flight speedat which the aircraft is controllable in the landing configuration3.2.36 VRground gust speed3.2.37 VTmaximum aerotow speed3.2.38 VWmaximum winch tow speed3.2.39 VYspeed for best rate of climb3.2.40 Wmaximum takeoff or maximum design
22、 weight(kg)3.2.41 WEmaximum empty aircraft weight (kg)3.2.42 WUminimum useful load (kg)3.2.43 waverage design surface load (N/m2)4. Flight4.1 Proof of Compliance:4.1.1 Each of the following requirements shall be met at themost critical weight and CG configuration. Unless otherwisespecified, the spee
23、d range from stall to VDFor the maximumallowable speed for the configuration being investigated shallbe considered.4.1.1.1 VDFshall be less than or equal to VD.4.1.1.2 If VDFchosen is less than VD, VNEmust be less thanor equal to 0.9 VDFand greater than or equal to 1.1 VC.4.1.2 The following toleran
24、ces are acceptable during flighttesting:Weight +5 %, 10 %Weight, when critical +5 %, 1 %CG 7 % of total travel4.2 Compliance must be established for all configurationsexcept as otherwise noted. In demonstrating compliance, thepowerplant or propeller, if retractable, must be retracted,except as other
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