ASTM F3093/F3093M-15
(Specification)Standard Specification for Aeroelasticity Requirements
Standard Specification for Aeroelasticity Requirements
SCOPE
1.1 This specification addresses the aeroelasticity requirements of the airplane.
1.2 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.
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Designation: F3093/F3093M −15
Standard Specification for
1
Aeroelasticity Requirements
This standard is issued under the fixed designation F3093/F3093M; the number immediately following the designation indicates the year
of original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval.
A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 3. Terminology
1.1 This specification addresses the aeroelasticity require- 3.1 Definitions:
ments of the airplane. 3.1.1 GVT—ground vibration testing
1.2 The values stated in either SI units or inch-pound units 3.1.2 V-n—velocity versus load factor
are to be regarded separately as standard. The values stated in
each system may not be exact equivalents; therefore, each 4. Flutter
system shall be used independently of the other. Combining
4.1 It must be shown by the methods in 4.2, and either 4.3
values from the two systems may result in non-conformance
or4.4,thattheairplaneisfreefromflutter,controlreversal,and
with the standard.
divergence for any condition of operation within the limit V-n
1.3 This standard does not purport to address all of the
envelope and at all speeds up to the speed specified for the
safety concerns, if any, associated with its use. It is the
selected method. In addition:
responsibility of the user of this standard to establish appro-
4.1.1 Adequate tolerances must be established for quantities
priate safety and health practices and determine the applica-
which affect flutter, including speed, damping, mass balance,
bility of regulatory limitations prior to use.
and control system stiffness; and
4.1.2 Thenaturalfrequenciesofmainstructuralcomponents
2. Referenced Documents
must be determined by vibration tests or other approved
2
methods. This determination is not required for Level 1
2.1 ASTM Standards:
airplanes with V up to 260 kph [140 knots] CAS and
F3061 Specification for Systems and Equipment in Small
D
maximum gross weight up to 750 kg [1650 lbm].
Aircraft
F3065/F3065M Specification for Installation and Integration
4.2 Flight flutter tests must be made to show that the
of Propeller Systems
airplane is free from flutter, control reversal, and divergence,
F3115 Specification for Structural Durability for Small Air-
and to show that:
planes
4.2.1 Proper and adequate attempts to induce flutter have
3
2.2 Federal Aviation Administration (FAA) Document:
been made within the speed range up to V /M (or V /M
D D DF DF
Airframe and Equipment Engineering Report No. 45 (as for jets);
corrected) “Simplified Flutter Prevention Criteria” 1955
4.2.2 The vibratory response of the structure during the test
4
indicates freedom from flutter;
2.3 Federal Aviation Regulations:
4.2.3 A proper margin of damping exists at V /M (or
14 CFR 23 Amendment 62
D D
V /M for jets); and
DF DF
4.2.4 As V /M (or V /M for jets) is approached, there
D D DF DF
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral is no large or rapid reduction in damping.
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on
4.3 Any rational analysis used to predict freedom from
Structures.
Current edition approved May 1, 2015. Published August 2015. DOI: 10.1520/ flutter, control reversal, and divergence must cover all speeds
F3093_F3093M-15.
up to 1.2 V /1.2 M , limited to Mach 1.0 for subsonic
D D
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
airplanes.
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
4.4 Compliance with rigidity and mass balance criteria
the ASTM website.
defined in pages 4-12 of FAA’s Airframe and Equipment
3
Available from Federal Aviation Administration (FAA), 800 Independence
Engineering Report No. 45 may be accomplished to show that
Ave., SW, Washington, DC 20591, http://www.faa.gov.Available from U.S. Gov-
ernment Printing Office Superintendent of Documents, 732 N. Capitol St., NW, Mail
the airplane is free from flutter, control reversal, or divergence
Stop: SDE, Washington, DC 20401, http://www.access.gpo.gov.
if:
4
Available from U.S. Government Printing Office Superintendent of Documents,
4.4.1 V /M for the airplane is less than 480 kph [260
732 N. Capitol St., NW, Mail Stop: SDE, Washington, DC 20401, http:// D D
www.access.gpo.gov. knots] (EAS) and less than Mach 0.5,
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
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F3093/F3093M − 15
4.4.2 The wing and aileron flutter prevention criteria, as 4.7 For airplanes showing compliance with the fail-safe
represented by the wing torsional stiffness and aileron balance crit
...
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