1、Designation: F3093/F3093M 15Standard Specification forAeroelasticity Requirements1This standard is issued under the fixed designation F3093/F3093M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revision. A number
2、 in parentheses indicates the year of last reapproval.A superscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification addresses the aeroelasticity require-ments of the airplane.1.2 The values stated in either SI units or inch-pound unitsare
3、 to be regarded separately as standard. The values stated ineach system may not be exact equivalents; therefore, eachsystem shall be used independently of the other. Combiningvalues from the two systems may result in non-conformancewith the standard.1.3 This standard does not purport to address all
4、of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:2F3061 Specification fo
5、r Systems and Equipment in SmallAircraftF3065/F3065M Specification for Installation and Integrationof Propeller SystemsF3115 Specification for Structural Durability for Small Air-planes2.2 Federal Aviation Administration (FAA) Document:3Airframe and Equipment Engineering Report No. 45 (ascorrected)
6、“Simplified Flutter Prevention Criteria” 19552.3 Federal Aviation Regulations:414 CFR 23 Amendment 623. Terminology3.1 Definitions:3.1.1 GVTground vibration testing3.1.2 V-nvelocity versus load factor4. Flutter4.1 It must be shown by the methods in 4.2, and either 4.3or 4.4, that the airplane is fre
7、e from flutter, control reversal, anddivergence for any condition of operation within the limit V-nenvelope and at all speeds up to the speed specified for theselected method. In addition:4.1.1 Adequate tolerances must be established for quantitieswhich affect flutter, including speed, damping, mass
8、 balance,and control system stiffness; and4.1.2 The natural frequencies of main structural componentsmust be determined by vibration tests or other approvedmethods. This determination is not required for Level 1airplanes with VDup to 260 kph 140 knots CAS andmaximum gross weight up to 750 kg 1650 lb
9、m.4.2 Flight flutter tests must be made to show that theairplane is free from flutter, control reversal, and divergence,and to show that:4.2.1 Proper and adequate attempts to induce flutter havebeen made within the speed range up to VD/MD(or VDF/MDFfor jets);4.2.2 The vibratory response of the struc
10、ture during the testindicates freedom from flutter;4.2.3 A proper margin of damping exists at VD/MD(orVDF/MDFfor jets); and4.2.4 As VD/MD(or VDF/MDFfor jets) is approached, thereis no large or rapid reduction in damping.4.3 Any rational analysis used to predict freedom fromflutter, control reversal,
11、 and divergence must cover all speedsup to 1.2 VD/1.2 MD, limited to Mach 1.0 for subsonicairplanes.4.4 Compliance with rigidity and mass balance criteriadefined in pages 4-12 of FAAs Airframe and EquipmentEngineering Report No. 45 may be accomplished to show thatthe airplane is free from flutter, c
12、ontrol reversal, or divergenceif:4.4.1 VD/MDfor the airplane is less than 480 kph 260knots (EAS) and less than Mach 0.5,1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.30 onStructures.Current edition
13、approved May 1, 2015. Published August 2015. DOI: 10.1520/F3093_F3093M-15.2For referenced ASTM standards, 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
14、ASTM website.3Available from Federal Aviation Administration (FAA), 800 IndependenceAve., SW, Washington, DC 20591, http:/www.faa.gov.Available from U.S. Gov-ernment Printing Office Superintendent of Documents, 732 N. Capitol St., NW, MailStop: SDE, Washington, DC 20401, http:/www.access.gpo.gov.4Av
15、ailable from U.S. Government Printing Office Superintendent of Documents,732 N. Capitol St., NW, Mail Stop: SDE, Washington, DC 20401, http:/www.access.gpo.gov.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States14.4.2 The wing and aileron
16、 flutter prevention criteria, asrepresented by the wing torsional stiffness and aileron balancecriteria, are limited in use to airplanes without large massconcentrations (such as engines, floats, or fuel tanks in outerwing panels) along the wing span, and4.4.3 The airplane does not have a T-tail or
17、other unconven-tional tail configurations, does not have unusual mass distribu-tions or other unconventional design features that affect theapplicability of the criteria, and has fixed-fin and fixed-stabilizer surfaces.4.5 For turbopropeller-powered airplanes, the dynamicevaluation must include:4.5.
18、1 Whirl mode degree of freedom which takes intoaccount the stability of the plane of rotation of the propellerand significant elastic, inertial, and aerodynamic forces.4.5.2 Propeller, engine, engine mount, and airplane structurestiffness and damping variations appropriate to the particularconfigura
19、tion.4.6 Freedom from flutter, control reversal, and divergenceup to VD/MDmust be shown as follows:4.6.1 For airplanes that meet the criteria of sections 4.4.1through 4.4.3 of this section, after the failure, malfunction, ordisconnection of any single element in any tab control system.4.6.2 For airp
20、lanes other than those described in section4.6.1 of this section, after the failure, malfunction, or discon-nection of any single element in the primary flight controlsystem, any tab control system, or any flutter damper.4.7 For airplanes showing compliance with the fail-safecriteria of Specificatio
21、n F3115, the airplane must be shown byanalysis to be free from flutter up to VD/MDafter fatiguefailure, or obvious partial failure, of a principal structuralelement.4.8 For airplanes showing compliance with the damagetolerance criteria of Specification F3115, the airplane must beshown by analysis to
22、 be free from flutter up to VD/MDwith theextent of damage for which residual strength is demonstrated.4.9 For modifications to the type design that could affect theflutter characteristics, compliance with 4.1 must be shown,except that analysis based on previously approved data may beused alone to sh
23、ow freedom from flutter, control reversal anddivergence, for all speeds up to the speed specified for theselected method.4.10 Additional flutter requirements are addressed in thefollowing standards:4.10.1 Tab controls requirements including flutter are de-fined in Specification F3061.4.10.2 Spring d
24、evices requirements including flutter aredefined in Specification F3061.4.10.3 Propeller requirements including flutter are definedin Specification F3065/F3065M.4.10.4 Ice protection requirements including flutter are de-fined in 14 CFR 23.1419.ASTM International takes no position respecting the val
25、idity 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 responsibility.This standard is sub
26、ject to revision at any time by the responsible technical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn. Your comments are invited either for revision of this standard or for additional standardsand should be addressed to ASTM International Headqua
27、rters. Your comments will receive careful consideration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to the ASTM Committee on Standards, at the address shown below.This standa
28、rd is copyrighted by ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at the aboveaddress or at 610-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM website(www.astm.org). Permission rights to photocopy the standard may also be secured from the Copyright Clearance Center, 222Rosewood Drive, Danvers, MA 01923, Tel: (978) 646-2600; http:/ 152
