ASTM F3114-2015 Standard Specification for Structures《结构的标准规格》.pdf
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1、Designation: F3114 15Standard Specification forStructures1This standard is issued under the fixed designation F3114; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the y
2、ear of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification addresses the structural requirementsthat apply to all portions of the airframe regardless ofcomponent, system, or structure.1.2 This specification was o
3、riginally conceived for smallairplanes as defined in the F44 terminology standard but mayfind broader applicability. Use of the term aircraft throughoutthis specification is intended to allow the relevant CAA(s) toaccept this standard as a means of compliance as theydetermine it to be appropriate, w
4、hether for small airplanes orfor other types of aircraft.1.3 The applicant for a design approval must seek individualguidance from their respective CAA body concerning the useof this standard as part of a certification plan. For informationon which CAA regulatory bodies have accepted this standard(i
5、n whole or in part) as a means of compliance to their SmallAirplane Airworthiness Rules (hereinafter referred to as “theRules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.1.4 This standard does not purport to address all of thesafety concerns, if any
6、, 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:2F3060 Terminology for AircraftF3061 Specification f
7、or Systems and Equipment in SmallAircraftF3083 Specification for Emergency Conditions, OccupantSafety and AccommodationsF3093 Specification for Aeroelasticity RequirementsF3115 Specification for Structural Durability for Small Air-planesF3116 Specification for Design Loads and Conditions3. Terminolo
8、gy3.1 See Terminology F3060 for more definitions and abbre-viations.4. Strength4.1 LoadsStrength requirements are specified in terms oflimit loads (the maximum loads to be expected in service) andultimate loads (limit loads multiplied by prescribed factors ofsafety).4.2 Factor of SafetyUnless otherw
9、ise provided, a factor ofsafety of 1.5 must be used.4.3 Strength and Deformation:4.3.1 The structure must be able to support limit loadswithout detrimental, permanent deformation. At any load up tolimit loads, the deformation may not interfere with safeoperation.4.3.2 The structure must be able to s
10、upport ultimate loadswithout failure for at least three seconds, except local failuresor structural instabilities between limit and ultimate load areacceptable only if the structure can sustain the requiredultimate load for at least three seconds. However when proof ofstrength is shown by dynamic te
11、sts simulating actual loadconditions, the three second limit does not apply.4.4 Proof of Structure:4.4.1 Compliance with the strength and deformation re-quirements of 4.3 must be shown for each critical loadcondition. Structural analysis may be used only if the structureconforms to those for which e
12、xperience has shown this methodto be reliable. In other cases, substantiating load tests must bemade. Dynamic tests, including structural flight tests, areacceptable if the design load conditions have been simulated.4.4.2 Certain parts of the structure must be tested asspecified.4.5 Vibration and Bu
13、ffetingThere must be no vibration orbuffeting severe enough to result in structural damage, andeach part of the airplane must be free from excessive vibration,under any appropriate speed and power conditions up toVD/MD,orVDF/MDFfor turbojets.1This specification is under the jurisdiction ofASTM Commi
14、ttee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.30 onStructures.Current edition approved Nov. 1, 2015. Published December 2015. DOI:10.1520/F3114-15.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serv
15、iceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States14.6 Canard or Tandem Wing Configurations:4.6.1 The forwa
16、rd structure of a canard or tandem wingconfiguration must:4.6.1.1 Meet all requirements of this standard, Specifica-tions F3116, F3093, F3083, and F3115 applicable to a wing;and4.6.1.2 Must meet all requirements applicable to the func-tion performed by these surfaces.4.7 Windshields and Windows:4.7.
17、1 The internal panels of windshields and windows mustbe constructed of a nonsplintering material, such as but notlimited to:4.7.1.1 Nonsplintering safety glass; or4.7.1.2 Synthetic resins.4.7.2 The design of windshields, windows, and canopies inpressurized airplanes must be based on factors peculiar
18、 to highaltitude operation, including:4.7.2.1 The effects of continuous and cyclic pressurizationloadings;4.7.2.2 The inherent characteristics of the material used; and4.7.2.3 The effects of temperatures and temperature gradi-ents.4.7.3 On pressurized airplanes, if certification for operationup to a
19、nd including 25 000 ft is requested, an enclosure canopyincluding a representative part of the installation must besubjected to special tests to account for the combined effects ofcontinuous and cyclic pressurization loadings and flight loads,or compliance with the fail-safe requirements of 4.7.4 mu
20、st beshown.4.7.4 If certification for operation above 25 000 ft isrequested, the windshields, window panels, and canopies mustbe strong enough to withstand the maximum cabin pressuredifferential loads combined with critical aerodynamic pressureand temperature effects, after failure of any load-carry
21、ingelement of the windshield, window panel, or canopy.4.7.5 In the event of any probable single failure, a transpar-ency heating system must be incapable of raising the tempera-ture of any windshield or window to a point where there wouldbe:4.7.5.1 Structural failure that adversely affects the integ
22、rityof the cabin; or4.7.5.2 A danger of fire.4.7.6 In addition, for Level 4 airplanes, the followingapplies:4.7.6.1 Windshield panes directly in front of the pilots in thenormal conduct of their duties, and the supporting structuresfor these panes, must withstand, without penetration, theimpact of a
23、 2-lb bird when the velocity of the airplane (relativeto the bird along the airplanes flight path) is equal to theairplanes maximum approach flap speed.4.8 Landing Gear:4.8.1 For Level 4 airplanes, the following general require-ments for the landing gear apply:4.8.1.1 Each airplane must be designed
24、so that, with theairplane under control, it can be landed on a paved runway withany one or more landing-gear legs not extended withoutsustaining a structural component failure that is likely to causethe spillage of enough fuel to constitute a fire hazard.4.8.1.2 Compliance with the provisions of thi
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