ASTM F355-2010a Standard Test Method for Impact Attenuation of Playing Surface Systems and Materials《游戏台面系统和材料的撞击衰减性能的标准试验方法》.pdf

《ASTM F355-2010a Standard Test Method for Impact Attenuation of Playing Surface Systems and Materials《游戏台面系统和材料的撞击衰减性能的标准试验方法》.pdf》由会员分享，可在线阅读，更多相关《ASTM F355-2010a Standard Test Method for Impact Attenuation of Playing Surface Systems and Materials《游戏台面系统和材料的撞击衰减性能的标准试验方法》.pdf（6页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: F355 10aAn American National StandardStandard Test Method forImpact Attenuation of Playing Surface Systems andMaterials1This standard is issued under the fixed designation F355; the number immediately following the designation indicates the year of originaladoption or, in the case of re

2、vision, the year of last revision. A number in parentheses indicates the year of last reapproval. A superscriptepsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This test method measures the impact attenuation ofplaying surface systems and materials, specific

3、ally the peakimpact acceleration (“impact shock”) produced under pre-scribed impact conditions.1.2 This test method is applicable to natural and artificialplaying surface systems intended to provide impact attenua-tion, including natural and artificial turf sports fields andplayground surfaces.1.3 T

4、his test method is applicable to impact attenuatingmats and padding used in sports facilities, including stadiumwall padding, gymnastic mats and wrestling mats.1.4 This test method may be used to measure the impactattenuation of materials and components used as protectivepadding on trampoline frames

5、, goal posts, etc., provided thematerial or component can be tested separately from theequipment to which it is attached.1.5 Without modifications, this test method shall not be usedto test materials and components that are attached to structuresor equipment or finished products, unless the impact a

6、ttenua-tion of the whole system is of interest.1.6 While it is widely believed that appropriate impactattenuation can reduce the risk of impact-related injuries, therelationships between the results of this test method andspecific injury risk and outcomes have not been determined.1.7 The values stat

7、ed in SI units are to be regarded as thestandard. The values given in parentheses are for informationonly.1.8 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 establish appro-priate safety an

8、d health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:2D1596 Test Method for Dynamic Shock Cushioning Char-acteristics of Packaging MaterialE105 Practice for Probability Sampling of MaterialsE122 Practice for Calculating

9、Sample Size to Estimate,With Specified Precision, the Average for a Characteristicof a Lot or ProcessE691 Practice for Conducting an Interlaboratory Study toDetermine the Precision of a Test MethodF1292 Specification for Impact Attenuation of SurfacingMaterials Within the Use Zone of Playground Equi

10、pmentF2650 Terminology Relating to Impact Testing of SportsSurfaces and Equipment2.2 SAE Standard:SAE J211/1 Instrumentation for Impact Tests - Part 1 -Electronic Instrumentation (rev. July 2007)33. Terminology3.1 Definitions:3.1.1 Definitions of terms related to impact testing of sportssurfaces equ

11、ipment can be found in Terminology F2650.4. Summary of Test Method4.1 A test specimen is impacted at a specified velocity witha missile of given mass and geometry. An accelerometermounted in the missile is used to record the acceleration-timehistory of the impact and the peak acceleration is used as

12、 ameasure of impact severity. Optionally, the displacement his-tory of the impact may also be recorded.4.2 This test method defines three missiles for use in playingsurface impact tests:1This test method is under the jurisdiction of ASTM Committee F08 on SportsEquipment and Facilities and is the dir

13、ect responsibility of Subcommittee F08.52 onMiscellaneous Playing Surfaces.Current edition approved July 1, 2010. Published August 2010. Originallyapproved in 1972. Last previous edition approved in 2010 as F355 10. DOI:10.1520/F0355-10A.2For referenced ASTM standards, visit the ASTM website, www.as

14、tm.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.3Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096-0001, http:/www.sae.org.1Copyright ASTM

15、International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.4.2.1 Missiles A and D are both cylindrical, with specifiedmass and geometry and a circular, flat, metal impactingsurface. These missiles are used with a guidance mechanism.4.2.2 Missile E has a hemisp

16、herical impacting surface ofspecified mass and geometry and may be used with a guidancesystem or, if equipped with a triaxial accelerometer, withoutguidance (“free-fall”).4.2.3 The specific masses and geometries of the missiles aredetailed in 6.2.5. Significance and Use5.1 The results of this method

17、 quantify the impact attenua-tion of playing surface and system specimens under the specifictest conditions.5.2 The test method measures the outcome of impactsperformed under specific conditions. It does not quantify theintrinsic material properties of the tested specimens.5.3 Test results from diff

18、erent specimens obtained under thesame conditions (that is, the same missile mass and geometry,drop height, etc.) may be used to compare impact attenuationunder those conditions.5.4 Test results obtained under different conditions are notcomparable. Specifically obtained with different missiles aren

19、ot equivalent and cannot be directly compared. Similarly, testresults obtained using the same missile, but using differentdrop heights, are not directly comparable.6. Apparatus6.1 AnvilFor tests performed on surface samples in alaboratory, the surface sample shall be mounted on a rigid anvilor base

20、having a mass at least 100 times that of the missile.6.2 Impact Test SystemA device or system for performingan impact test in which an instrumented missile is dropped ontoa playing surface or surfacing material from a predetermineddrop height.6.2.1 Missile:6.2.1.1 The missile shall have one of the c

21、ombinations ofmass and geometry specified in Table 1. (See also Fig. 1.)6.2.1.2 The missile may include cavities and additionalcomponents required to accommodate the attachment of sen-sors or to attach a supporting assembly. The form of anycavities or additional components shall be generally symmetr

22、i-cal about the Z-axis of the level missile such that center ofmass lies within 0.08 in. (2 mm) of the Z-axis and the momentsof inertia about any two horizontal axes do not differ by morethan 5 %.6.2.1.3 A supporting assembly (for example, a handle orball arm) may be rigidly attached to the missile

23、as a means ofconnecting it to an external guidance system. The total mass ofthe drop assembly, which is the combined mass of the missile,accelerometer and supporting assembly shall be that defined inTable 1. The mass of the supporting assembly alone shall notexceed 30 % of the total mass.6.2.2 Guida

24、nce Mechanism for Guided Impact TestsForguided impact tests; the missile may be connected to low-friction guides (such as a monorail, dual rails, or guide wires)using a follower or other mechanism in order to constrain thefall trajectory of the missile to a vertically downward path.Missile A and D m

25、ay be guided using a ventilated tube. Theguidance system must allow the missile to be leveled prior toa drop and must maintain the missile in a level (65) attitudeduring the drop. The guidance mechanism shall be constructedin a manner that that does not impede the trajectory of themissile during its

26、 fall or during its contact with the surfacebeing tested; other than necessary impedance caused byfriction in the guidance mechanism.6.2.3 Support Structure for Free-Fall Impact TestsForfree-fall impact tests, a support structure (for example, a tripod)shall be used to ensure repeatable drop height

27、and location. Thesupport structure shall be sufficiently rigid to support theweight of the missile without visible deformation. The supportstructure shall be erected in a manner that does not impede thetrajectory of the missile during its fall or during its contact withthe surface being tested.6.2.4

28、 Drop Height Control MechanismThe guidancemechanism of 6.2.2 or the support structure of 6.2.3 shallincorporate a means of repeatedly positioning the missile at apredetermined drop height.6.2.5 Release MechanismThe operation of any releasemechanism provided as a means of initiating a drop of themiss

29、ile shall not influence the fall trajectory of the missilefollowing release.6.3 Acceleration Measurement SystemA transducer ortransducers and associated equipment for measuring and re-cording the acceleration of the missile during an impact with anaccuracy of within 61 % of the true value.TABLE 1 Mi

30、ssile Mass and GeometryMissile ImpactingSurfaceShapeMass GeometryA Cylindrical 9.1 6 0.050 kg(20.0 6 0.11 lb)Circular face with an area of 129 62.0-cm2(20 6 1.0-in.2) and acircumference-relieved radius of 2 60.25 mm (0.08 6 0.01 in.) toeliminate sharp edgesD Cylindrical 2.25 6 0.050 kg(4.95 6 0.011

31、lb)Circular face with a diameter of 506 0.1 mm (1.97 6 0.04 in.) and acircumference-relieved radius of0.75 6 0.25 mm (0.03 6 0.01 in.) toeliminate sharp edgesE Hemispherical 4.6 6 0.02 kg(10.1 6 0.05 lb)Hemispherical face with a diameterof 160 6 2mm(6.36 0.1 in.)F355 10a26.3.1 AccelerometersAn accel

32、erometer shall be rigidlyattached at the center of mass of the missile. The sensing axisor axes of the accelerometer shall pass through the center ofmass of the missile.6.3.1.1 For a free-fall test, a triaxial accelerometer is re-quired.6.3.1.2 For a guided test, a single uniaxial accelerometermay b

33、e used. The accelerometer shall be rigidly attached at thecenter of mass of the missile (62 mm) with its axis ofsensitivity aligned (65) with the missiles Z axis and passingthrough the center of mass of the missile.6.3.2 Accelerometers shall have a minimum sensitive rangeof 6500 g and be capable of

34、tolerating accelerations of at least1000 g along any axis.6.3.3 Accelerometer CalibrationAccelerometers shall becalibrated by reference to a National Institute of Standards andTechnology (NIST) traceable standard using a shaker table toexcite a range of frequencies and amplitudes determinedsuitable

35、by the accelerometer manufacturer. The calibrationprocedure shall include, as a minimum, the range of frequen-cies from 2 to 2000 Hz.NOTE 1Accelerometer calibration is usually performed by the manu-facturer.6.3.4 Accelerometers shall be recalibrated at a time intervalrecommended by the equipment man

36、ufacturer or every twoyears, which ever is the lesser time interval.6.3.5 Accelerometer ConnectionsThe means of providingpower and signal connections to the accelerometer (for ex-ample, a cable) shall be constructed in a manner such that theconnecting devices do not influence the trajectory of themi

37、ssile before or during the impact test.6.3.6 Accelerometer Signal ConditioningAny signal con-ditioning of amplifying electronics required for proper opera-tion of accelerometers shall be of a type recommended by theaccelerometer manufacturer and shall have impedance andfrequency response characteris

38、tics that are compatible with theaccelerometer.6.3.7 Accelerometer Signal Filtering:6.3.7.1 Anti-Aliasing FilterTo prevent aliasing in thedigitized acceleration data, the acceleration signals shall befiltered with an analog low pass filter prior to digitization. Theanti-aliasing filter shall have a

39、corner frequency of 5000 6 500Hz or a maximum of 0.253 the single channel sampling rate.6.3.7.2 Data Channel FilterDigitized data shall be fil-tered in accordance with the specification for an SAE ChannelClass 1000 data channel, using a 4th order Butterworth. AnFIG. 1 Schematics Showing Approximate

40、Relative Geometries of the A, D, and E MissilesF355 10a3analog filter may be substituted provided it has 4-pole charac-teristics and conforms to the data channel specification.6.3.8 Recording DeviceA digital recording device such asa digital storage oscilloscope, a dedicated waveform analyzerof a co

41、mputer equipped with an analog to digital convertershall be used to capture the acceleration time signal producedduring an impact. Analog oscilloscopes and other analogrecording devices shall not be used.6.3.9 ResolutionThe conversion from analog accelerom-eter signal to digital data shall be accomp

42、lished with a digitizerhaving a resolution of 0.25 g or less. (For example, a twelve bitdigitizer spanning the range 6500 g has a resolution of 0.244g.)6.3.10 Sample RateThe minimum sampling rate of therecording device shall be 10.0 kHz per accelerometer channel.When a triaxial accelerometer is used

43、, three individual digitiz-ers (one per accelerometer axis), each with a minimumsampling rate of 10 kHz are required.6.3.11 CapacityThe digitizer shall be capable of record-ing and storing data continuously for a minimum of 50 ms,beginning at least 5 ms before onset of the impact and endingno earlie

44、r than 5 ms after the cessation of the impact.6.3.12 DisplayThe recording system shall have the capa-bility of displaying the recorded acceleration-time data in orderto allow inspection by the operator. A graphical display isrecommended, but a tabular printout or other form of display isacceptable.

45、The display shall allow inspection of all the datapoints recorded from at least 5 ms before the onset of impactuntil no less than 5 ms after cessation of the impact. Thedisplay shall show acceleration data in a manner that allowsinspection of all data points lying in the acceleration rangefrom 10 g

46、to a value that exceeds the maximum recordedacceleration value.6.3.13 Accelerometer Data Channels:6.3.13.1 AccuracyThe accuracy of the each data channelshall be such that the maximum acceleration recorded duringan impact is recorded is within 61 % of the true value.6.3.13.2 Frequency ResponseAll acc

47、eleration data chan-nels, before signal filtering, shall have a flat frequency response60.1 dB in a range extending from below a maximum of 1.0Hz to above a minimum of 2000 Hz.6.3.13.3 Channel Frequency ClassAll acceleration datachannels, including signal filtering, shall, as a minimum,conform to th

48、e requirements of a Channel Frequency Class1000 data channel, as specified by SAE J211/1.6.4 Drop Height MeasurementA means of repeatablydetermining the missiles drop height with a resolution of 1 in.(25 mm) and to an accuracy of 61 % of the true value isrequired.6.4.1 For a free-fall impact test, t

49、he drop height shall bemeasured directly, prior to release of the missile, using ameasuring stick, a steel tape or other appropriate means wherepossible. An indirect means of determining the theoretical dropheight shall also be used. Such indirect means may comprisethe velocity measuring system described in 6.4.2, or a means ofmeasuring the time interval between release of the missile andthe onset of impact (the fall time), in which case the timeinterval shall be determined with a resolution and accuracy of1.0 ms. Both the measured drop height and the