1、Designation: F 2564 06Standard Specification forDesign and Performance of a Light Sport Glider1This standard is issued under the fixed designation F 2564; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A
2、 number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) 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 “gli
3、der.”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 wit
4、h a 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 pl
5、ant 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 e
6、stablish appro-priate safety and health practices and determine the applica-bility of regulatory requirements prior to use.2. Referenced Documents2.1 ASTM Standards:2F 2279 Practice for Quality Assurance in the Manufactureof Light Sport AirplanesF 2295 Practice for Continued Operational Safety Monit
7、or-ing of a Light Sport AirplaneF 2316 Specification for Airframe Emergency Parachutesfor Light Sport AircraftF 2339 Practice for Design and Manufacture of Reciprocat-ing Spark Ignition Engines for Light Sport Aircraft3. Terminology3.1 Definitions:3.1.1 flapsany movable high lift device.3.1.2 maximu
8、m empty weight, WE(kg)largest emptyweight of the glider, including all operational equipment that isinstalled in the glider: weight of the airframe, powerplant,required equipment, optional and specific equipment, fixedballast, full engine coolant and oil, hydraulic fluid, and theunusable fuel. Hence
9、, the maximum empty weight equalsmaximum takeoff weight minus minimum useful load:WE= W WU.3.1.3 minimum useful load, WU(kg)where WU= W WE.3.2 Abbreviations:3.2.1 AOIAircraft Operating Instructions3.2.2 ARAspect Ratio = b2/S3.2.3 bwing span (m)3.2.4 cchord (m)3.2.5 CAScalibrated air speed (m/s, kts)
10、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 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/s
11、23.2.13 IASindicated air speed (m/s, kts)3.2.14 ICAOInternational Civil Aviation Organization3.2.15 LSAlight sport aircraft3.2.16 nload factor3.2.17 n1glider positive maneuvering limit load factorat VA3.2.18 n2glider positive maneuvering limit load factorat VD3.2.19 n3glider negative maneuvering lim
12、it 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 area (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 VDFdemonstrate
13、d flight diving speed (VDF# VD)3.2.28 VFdesign flap speed1This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the direct responsibility of Subcommittee F37.10 on Glider.Current edition approved May 1, 2006. Published May 2006.2For referenced ASTM standard
14、s, visit the ASTM website, www.astm.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.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 1
15、9428-2959, United States.3.2.29 VFEmaximum flap extended speed3.2.30 VHmaximum speed in level flight with maximumcontinuous power (corrected for sea level standard conditions)3.2.31 VLOmaximum speed for landing gear extended3.2.32 VNEnever exceed speed VH# VNE# 0.9 VDF!3.2.33 VSstalling speed or min
16、imum steady flight speed atwhich the aircraft is controllable (flaps retracted)3.2.34 VS1stalling speed or minimum steady flight speedwith the flaps in a specific configuration3.2.35 VS0stalling speed or minimum steady flight speedat which the aircraft is controllable in the landing configuration(fl
17、aps fully deployed)3.2.36 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 weight(kg)3.2.41 WEmaximum empty aircraft weight (kg)3.2.42 WUminimum useful load (kg)3.2.43 waverage design surfa
18、ce 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 speed range from stall to VDFor the maximumallowable speed for the configuration being investigated shallbe considered.
19、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 tolerances are acceptable during flighttesting:Weight +5 %, 10 %Weight, when critical +5 %, 1 %CG 67 % of total travel4.2
20、Compliance must be established for all configurationsexcept as otherwise noted. In demonstrating compliance, thepowerplant or propeller, if retractable, must be retracted,except as otherwise noted.4.3 Load Distribution Limits:4.3.1 The maximum flying weight shall be determined.4.3.1.1 The maximum we
21、ight must be determined so that itis:(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 and all requirements for flight characteristicsis shown.4.3.1.2 For a single-place
22、glider not less than the emptyweight of the glider, plus a weight of the occupant of 80 kg,plus the required minimum equipment, plus, for a poweredglider, sufficient fuel for at least 30 min of flight at maximumcontinuous power.4.3.1.3 For a two-place glider not less than the emptyweight of the glid
23、er, plus a weight of the occupants of 160 kg,plus the required minimum equipment, plus, for a poweredglider, sufficient fuel for at least 30 min of flight at maximumcontinuous 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
24、.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, corresponding CG, most for-ward, 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 w
25、hichcorresponds to that of a sole pilot weight of 65 kg up to themaximum flying weight, always considering the most unfavor-able placing of luggage.4.3.3.4 Fixed or removable ballast, or both, may be used ifproperly installed and placarded.4.4 Propeller Speed and Pitch Limits for a PoweredGliderThe
26、operating limitations shall not allow the engine toexceed safe operating 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
27、during aglide at VNEwith throttle closed.4.5 Performance, GeneralAll 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 VS0a
28、nd VSshall bedetermined by flight test at a rate of speed decrease of 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 positi
29、on, and the cowl flaps closed.4.5.1.3 For powered gliders, wings level, 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
30、 Glider:4.5.2.1 With the glider at maximum takeoff weight and fullthrottle, 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 flap
31、posi-tion, shall be specified within the AOI.4.5.3 ClimbAt maximum takeoff 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).F25640624.5.4 High Speed DescentIf so equipped, the glider
32、mustnot exceed VNEin a dive at a 30 angle to the horizon withairbrakes extended.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 Landin
33、g distance from 15 m (50 ft) above groundwhen speed at 15 m (50 ft) is 1.3 VS0.4.5.6.2 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
34、 VDFor themaximum allowable speed for the configuration being inves-tigated, engine 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.
35、4.6.1.3 Full control shall be maintained when retracting andextending flaps within 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 aircr
36、afttrimmed as closely as possible for steady flight at 1.3 VS1,itmust be possible 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 sh
37、all increase with in-creasing load factor.4.6.2.3 Longitudinal control must be maintained:(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 flapconf
38、iguration is made during steady horizontal flight at 1.1 VS1with simultaneous application of maximum continuous power.(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 di
39、rection of a turn with a 45 bank to the oppositedirection within b/3 or 4 s, whichever 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,
40、 rapid entry into orrecovery from a maximum cross-controlled slip shall not resultin 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 de
41、monstrated at speeds up to VTwithout:(1) Difficulty in regaining the normal towing 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
42、.6.4.3 A suitable range of tow cables must be established.4.6.4.4 Tests must be repeated for each location of thetowing release mechanism.4.6.5 Winch Launching:4.6.5.1 If the glider is equipped for winch launching orauto-tow launching, such launches must be demonstrated up toVWwithout:(1) Uncontroll
43、ed roll after leaving the ground and upon arelease,(2) Uncontrolled pitching oscillations, and(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 tr
44、imming 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 app
45、roach will not causecontrol forces in excess of those listed in Table 1 or excessivecontrol displacements, nor affect the controllability of theglider.4.6.6.3 After touchdown, there must not be a tendency toground loop, for pitching oscillation or to nose over.4.6.7 Static Longitudinal Stability:4.6
46、.7.1 The glider shall demonstrate the ability to trim forsteady flight at speeds appropriate to the launch, flight, andlanding approach configurations for gliders, and climb andcruise for powered gliders; at minimum and maximum weight;and forward and aft CG limits. If the glider has no in-flightadju
47、stable longitudinal trimming device, the trim speed mustbe between 1.2 VS1and 2.0 VS1for all CG positions.4.6.7.2 The glider shall exhibit positive longitudinal stabil-ity characteristics at any speed above VS1, up to the maximumallowable speed for the configuration being investigated, and atthe mos
48、t critical power setting and CG combination.4.6.7.3 Stability shall be shown by a tendency for the gliderto return toward steady flight after: (1) a “push” from steadyflight that results in a speed increase, followed by a non-abruptrelease of the pitch control; and (2) a “pull” from steady flighttha
49、t results in a speed decrease, followed by a non-abruptrelease of the pitch control.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 150 300 150For prolonged application: 20 15 100 Not determinedF25640634.6.7.4 The glider shall demonstrate compliance with thissection for the conditions listed in Table 2.4.6.7.5 While returning toward steady flight, the aircraft
