1、Designation: F355 10An 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 rev
2、ision, 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 covers the measurement of certainshock-absorbing characteristics, the impact force
3、-time relation-ships, and the rebound properties of playing surface systems.This test method is applicable to natural and artificial playingsurface systems and to components thereof. Typical playingsurfaces are wrestling mats, football fields, soccer fields,playgrounds, and so forth.NOTE 1This test
4、method may also be used to measure the shock-attenuation properties of materials used as protective padding, such as thepadding on trampoline frames, football goal posts, gymnasium wall,shoulder pads, body padding, and so forth. It should not be used, withoutsome modifications, to test the finished
5、products.1.2 The values stated in SI units are to be regarded as thestandard. The values given in parentheses are for informationonly.1.3 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 esta
6、blish appro-priate safety and 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 MaterialsE1
7、22 Practice for Calculating 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
8、 Use Zone of Playground EquipmentF2650 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 t
9、esting of sportssurfaces equipment 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
10、peak acceleration is used as 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:4.2.1 Missiles A and D are both cylindrical, with specifiedmass and geometry and a cir
11、cular, flat, metal impactingsurface. These missiles are used with a guidance mechanism.4.2.2 Missile E has a hemispherical 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 spec
12、ific masses and geometries of the missiles aredetailed in 6.2.5. Significance and Use5.1 The results of this method 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 c
13、onditions. It does not quantify theintrinsic material properties of the tested specimens.5.3 Test results from different specimens obtained under thesame conditions (that is, the same missile mass and geometry,1This test method is under the jurisdiction of ASTM Committee F08 on SportsEquipment and F
14、acilities and is the direct responsibility of Subcommittee F08.52 onMiscellaneous Playing Surfaces.Current edition approved April 15, 2010. Published May 2010. Originallyapproved in 1972. Last previous edition approved in 2009 as F355 09. DOI:10.1520/F0355-10.2For referenced ASTM standards, visit th
15、e 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.3Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096-0001, http:/www.sa
16、e.org.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.drop height, etc.) may be used to compare impact attenuationunder those conditions.5.4 Test results obtained under different conditions are notcomparable. Specifically obtained wi
17、th different missiles arenot 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 mounte
18、d on a rigid anvilor base 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 missi
19、le shall have one of the combinations 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
20、shall be generally symmetri-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 rigidl
21、y attached to the missile 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
22、the total mass.6.2.2 Guidance 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 downw
23、ard path.Missile A and D may 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 trajector
24、y of themissile during its 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 ensu
25、re repeatable drop height 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
26、surface being tested.6.2.4 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 in
27、itiating a drop of themissile 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
28、 the true value.6.3.1 AccelerometersAn accelerometer 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 guide
29、d test, a single uniaxial accelerometermay be 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
30、 sensitive rangeof 6500 g and be capable of 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 fr
31、equencies and amplitudes determinedsuitable by the accelerometer manufacturer. The calibrationprocedure shall include, as a minimum, the range of frequen-cies from 2 to 2000 Hz.TABLE 1 Missile Mass and GeometryMissile ImpactingSurfaceShapeMass GeometryA Cylindrical 9.1 6 0.050 kg(20.0 6 0.11 lb)Circ
32、ular 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 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
33、 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 102NOTE 2Accelerometer calibration is usually performed by the manu-facturer.6.3.4 Accelerometers shall be recalibrated at a time intervalrecomme
34、nded by the equipment manufacturer 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 influenc
35、e the trajectory of themissile 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 andfrequ
36、ency response characteristics 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-alia
37、sing filter shall have a 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. Ananalog filter
38、 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 computer equipped with an analog to digital convertershall be used to c
39、apture 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 accomplished with a digitizerhaving a resolution of 0.25 g or less. (For ex
40、ample, 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, three individual digitiz-ers (one per accelerometer axis), each wit
41、h 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 earlier than 5 ms after the cessation of the impact.FIG. 1 Schematics Showi
42、ng Approximate Relative Geometries of the A, D, and E MissilesF355 1036.3.12 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 o
43、f display isacceptable. 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 acce
44、leration rangefrom 10 g 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 F
45、requency ResponseAll acceleration 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
46、 a minimum,conform to the 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
47、free-fall impact test, the 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 veloci
48、ty 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 theoretical drophe
49、ight shall be reported.6.4.2 For a guided impact test, the theoretical drop heightmust be determined by measuring the velocity of the missileimmediately prior to the onset of an impact; at a point in themissiles trajectory no more than 2.0 in. (51 mm) above the firstpoint of contact between the missile and the surface under test.The velocity measuring system may consist of a light gatedevice to measure the time an opaque flag interrupts a lightsensor or other appropriate means. The velocity measuringdevice shall not interfere with or impede the traje
