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
25、wise noted.4.3 Load Distribution Limits:4.3.1 The maximum weight shall be determined so that it is:4.3.1.1 Not more than:(1) The highest weight selected by the applicant, and(2) The design maximum weight, which is the highestweight at which compliance with each applicable structuralloading condition
26、 and all requirements for flight characteristicsis shown.4.3.1.2 Not less than:(1) For a single-place glider not less than the empty weightof the glider, plus a weight of the occupant of 80 kg, plus therequired minimum equipment, plus, for a powered glider,sufficient energy (fuel or other energy sto
27、rage) for at least 30min of flight at maximum continuous power.(2) For a two-place glider not less than the empty weight ofthe glider, plus a weight of the occupants of 160 kg, plus therequired minimum equipment, plus, for a powered glider,sufficient energy (fuel or other energy storage) for at leas
28、t 30min of flight at maximum continuous power.4.3.2 The design empty weight shall be specified by themanufacturer.4.3.3 Empty Weight and Center of Gravity Range:4.3.3.1 The CG range within which the glider can be safelyoperated must be specified by the manufacturer.4.3.3.2 The empty weight, correspo
29、nding CG, mostforward, and most rearward CG shall be determined with fixedballast and required minimum equipment.4.3.3.3 The CG range must not be less than that whichcorresponds to that of a sole pilot weight of 65 kg up to themaximum weight, always considering the most unfavorableplacing of luggage
30、.4.3.3.4 Fixed or removable ballast, or both, may be used ifproperly installed and placarded.4.3.3.5 Multiple ESDs may be used if properly installed andplacarded.F2564 1324.4 Propeller Speed and Pitch Limits for a PoweredGliderThe operating limitations shall not allow the engine toexceed safe operat
31、ing limits established by the engine manu-facturer under normal conditions.4.4.1 Maximum RPM shall not be exceeded with fullthrottle during takeoff, climb, or flight at 0.9 VH, and 110 %maximum continuous RPM shall not be exceeded during aglide at VNEwith throttle closed.4.5 Performance, GeneralAll
32、performance requirementsapply in standard ICAO atmosphere in still air conditions andat sea level. Speeds shall be given in indicated (IAS) andcalibrated (CAS) airspeeds.4.5.1 Stalling Speeds:4.5.1.1 Wing level stalling speeds VS0and VSshall bedetermined by flight test at a rate of speed decrease of
33、 1 knot/sor less, throttle closed, with maximum takeoff weight, andmost unfavorable CG.4.5.1.2 For powered gliders, wing level stalling speeds VS0and VSshall also be determined with the engine idling,propeller in the takeoff position, and the cowl flaps closed.4.5.1.3 For powered gliders, wings leve
34、l, level flight topspeed VHshall be determined by flight test at maximumcontinuous rated RPM or with full throttle, if unable to reachmax continuous RPM, at maximum takeoff weight, in cruiseconfiguration.4.5.2 Takeoff for a Powered Glider:4.5.2.1 With the glider at maximum takeoff weight and fullthr
35、ottle, the distance to clear a 15-m (50-ft) obstacle shall notexceed 600 m (2000 ft).4.5.2.2 Takeoff must be demonstrated with crosswind com-ponents not less than 0.2 VS0.NOTE 1The procedure used for normal takeoff, including flapposition, shall be specified within the AOI.4.5.3 ClimbAt maximum take
36、off weight, flaps in theposition specified for climb within the AOI, landing gearretracted, and full throttle, the minimum rate of climb shallexceed 1.0 m/s (200 ft/min).4.5.4 High Speed DescentIf so equipped, the glider mustnot exceed VNEin a dive at a 30 angle to the horizon withairbrakes extended
37、.4.5.5 DescentIf so equipped, the glider must have a glideslope not flatter than one in seven at a speed of 1.3 VS0atmaximum weight and with airbrakes extended.4.5.6 LandingThe following shall be determined:4.5.6.1 Landing distance from 15 m (50 ft) above groundwhen speed at 15 m (50 ft) is 1.3 VS0.
38、4.5.6.2 Ground roll distance with braking if so equipped.4.6 Controllability and Maneuverability:4.6.1 General:4.6.1.1 The glider shall be safely controllable and maneu-verable during takeoff, climb, level flight, dive to VDFor themaximum allowable speed for the configuration beinginvestigated, engi
39、ne extension and retraction, and approach andlanding through the normal use of primary controls.4.6.1.2 Smooth transition between all flight conditions shallbe possible without exceeding pilot force as shown in Table 1.4.6.1.3 Full control shall be maintained when retracting andextending flaps withi
40、n their normal operating speed range (VS0to VFE).4.6.1.4 Lateral, directional, and longitudinal control shall bepossible down to VS0.4.6.2 Longitudinal Control:4.6.2.1 At steady flight, or if so equipped, with the aircrafttrimmed as closely as possible for steady flight at 1.3 VS1,itmust be possible
41、 at any speed below 1.3 VS1to pitch the nosedownward so that a speed not less than 1.3 VS1can be reachedpromptly. This must be shown with the aircraft in all possibleconfigurations.4.6.2.2 Longitudinal control forces shall increase with in-creasing load factor.4.6.2.3 Longitudinal control must be ma
42、intained:(1) In towed flight, while extending or retracting flaps.(2) When retraction or extension of the airbrakes is made atspeeds between 1.1 VS0and 1.5 VS0.(3) For powered gliders, when a change of the wing flapconfiguration is made during steady horizontal flight at 1.1 VS1 with simultaneous ap
43、plication of maximum continuouspower.(4) For powered gliders, when the engine is extended orretracted.4.6.3 Directional and Lateral Control:4.6.3.1 It must be possible, without significant slip or skid,to reverse the direction of a turn with a 45 bank to the oppositedirection within b/3 or 4 s, whic
44、hever is longer (where b is thespan of the glider in meters), when the turn is made at a speedof 1.4 VS1, with where applicable, wing flaps, air brakes, andlanding gear retracted.4.6.3.2 With and without flaps deployed, rapid entry into orrecovery from a maximum cross-controlled slip shall not resul
45、tin uncontrollable flight characteristics.4.6.3.3 Lateral and directional control forces shall not re-verse with increased deflection.4.6.4 Aerotowing:4.6.4.1 If the glider is equipped for aerotowing, aerotowsmust be demonstrated at speeds up to VTwithout:(1) Difficulty in regaining the normal towin
46、g position afterthe glider has been displaced laterally or vertically.(2) The released tow cable contacting any part of the glider.4.6.4.2 Aerotowing must be demonstrated with crosswindcomponents not less than 0.2 VS0.4.6.4.3 A suitable range of tow cables must be established.4.6.4.4 Tests must be r
47、epeated for each location of thetowing release mechanism.4.6.5 Winch Launching:TABLE 1 Pilot ForcePilot force as applied tothe controlsPitch,NRoll,NYaw,NWing flaps, landing gear,air brakes, retraction orextension of engine,two cable release,NFor temporary application:(less than 2 min) Stick200 150 3
48、00 150For prolonged application: 20 15 100 Not determinedF2564 1334.6.5.1 If the glider is equipped for winch launching orauto-tow launching, such launches must be demonstrated up toVWwithout:(1) Uncontrolled roll after leaving the ground and upon arelease,(2) Uncontrolled pitching oscillations, and
49、(3) Control forces in excess of those listed in Table 1 andexcessive deflections of the controls.4.6.5.2 Winch launching must be demonstrated with cross-wind components not less than 0.2 VS0.4.6.5.3 If a trimming device is fitted, the position usedduring the climb must be listed in the AOI.4.6.6 Approach and Landing:4.6.6.1 Normal approaches and landings until the glidercomes to a complete halt must be demonstrated with crosswindcomponents not less than 0.2 VS0.4.6.6.2 The use of air brakes during approach will not
