ASTM E1886-2013a Standard Test Method for Performance of Exterior Windows Curtain Walls Doors and Impact Protective Systems Impacted by Missile(s) and Exposed to Cyclic Pressure Di.pdf

《ASTM E1886-2013a Standard Test Method for Performance of Exterior Windows Curtain Walls Doors and Impact Protective Systems Impacted by Missile(s) and Exposed to Cyclic Pressure Di.pdf》由会员分享，可在线阅读，更多相关《ASTM E1886-2013a Standard Test Method for Performance of Exterior Windows Curtain Walls Doors and Impact Protective Systems Impacted by Missile(s) and Exposed to Cyclic Pressure Di.pdf（11页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: E1886 13E1886 13aStandard Test Method forPerformance of Exterior Windows, Curtain Walls, Doors, andImpact Protective Systems Impacted by Missile(s) andExposed to Cyclic Pressure Differentials1This standard is issued under the fixed designation E1886; the number immediately following the

2、 designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This test method covers t

3、he performance of exterior windows, curtain walls, doors, and impact protective systems impactedby missile(s) and subsequently subjected to cyclic static pressure differentials.Amissile propulsion device, an air pressure system,and a test chamber are used to model some conditions which may be repres

4、entative of windborne debris and pressures in awindstorm environment. This test method is applicable to the design of entire fenestration or impact protection systems assembliesand their installation. The performance determined by this test method relates to the ability of elements of the building e

5、nvelopeto remain unbreached during a windstorm.NOTE 1Exception: Exterior garage doors and rolling doors are governed by ANSI/DASMA 115 and are beyond the scope of this test method.1.2 The specifying authority shall define the representative conditions (see 10.1).1.3 The values stated in SI units are

6、 to be regarded as the standard. Values given in parentheses are for information only. Certainvalues contained in reference documents cited herein may be stated in inch-pound units and must be converted by the user.1.4 This standard does not purport to address all of the safety concerns, if any, ass

7、ociated with its use. It is the responsibilityof the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatorylimitations prior to use. Specific hazard statements are given in Section 7.2. Referenced Documents2.1 ASTM Standards:2E330 Tes

8、t Method for Structural Performance of Exterior Windows, Doors, Skylights and Curtain Walls by Uniform Static AirPressure DifferenceE631 Terminology of Building ConstructionsE997 Test Method for Structural Performance of Glass in Exterior Windows, Curtain Walls, and Doors Under the Influence ofUnifo

9、rm Static Loads by Destructive MethodsE1233 Test Method for Structural Performance of ExteriorWindows, Doors, Skylights, and CurtainWalls by CyclicAir PressureDifferentialE1996 Specification for Performance of Exterior Windows, Curtain Walls, Doors, and Impact Protective Systems Impacted byWindborne

10、 Debris in Hurricanes2.2 ANSI/ASCEASCE/SEI Standard:3ANSI/ASCEASCE/SEI 7 American Society of Civil Engineers Minimum Design Loads for Buildings and Other Structures2.3 American Lumber Standard:4Document PS20-94 American Softwood Lumber Standard2.4 ANSI/DASMA Standard:5ANSI/DASMA 115 Standard Method

11、for Testing Sectional Garage Doors and Rolling Doors: Determination of StructuralPerformance Under Missile Impact and Cyclic Wind Pressure1 This test method is under the jurisdiction ofASTM Committee E06 on Performance of Buildings and is the direct responsibility of Subcommittee E06.51 on Performan

12、ceof Windows, Doors, Skylights and Curtain Walls.Current edition approved Sept. 1, 2013Oct. 1, 2013. Published September 2013November 2013. Originally published in 1997. Last previous edition approved in 20052013as E1886 05.E1886 13. DOI: 10.1520/E1886-13.10.1520/E1886-13A.2 For referencedASTM stand

13、ards, visit theASTM website, www.astm.org, or contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standards Document Summary page on the ASTM website.3 Available from American Society of Civil Engineers (ASCE), 1801 Alexander Bell Dr., R

14、eston, VA 20191, http:/www.asce.org.4 Available from American Lumber Standard Committee, Inc. (ALSC), P.O. Box 210, Germantown, MD 20875-0210, http:/www.alsc.org.5 Available from Door fenestration; hurricanes; impact protective systems; missile impact; windborne debris; windstormsAPPENDIXES(Nonmanda

15、tory Information)X1. MISSILE PROPULSION DEVICESX1.1 For those wishing to use missile propulsion devices which have already been developed to launch certain types of missiles,the following apparatus are recommended:X1.2 Large Missile Air CannonThe large missile air cannon shall use compressed air to

16、propel the large missile. The cannonshall be capable of producing missile impact at the speeds defined in 6.2.7.2. The large missile cannon shall consist of four majorcomponents: a compressed air supply, a pressure release valve, a barrel and support frame, and a speed measuring system fordeterminin

17、g the missile speed.X1.2.1 The barrel of the large missile cannon shall consist of a 100-mm (4-in.) nominal inside diameter pipe and shall have alength at least as long as the missile. The total length of the barrel shall be the distance from the pressure valve to the vent holesin advance of the tim

18、ing system or to the mouth of the barrel. The barrel of the large missile cannon shall be mounted on a supportframe in a manner to facilitate aiming the missile so that it impacts the specimen at the desired location.X1.2.2 The large missile is defined in 6.2.7.2. The end of the missile that impacts

19、 the target is denoted as the missiles impact end.The end of the missile opposite to the impact end is denoted as the missiles trailing edge.Asabot shall be used at the trailing edgeof the missile to facilitate launching.X1.2.3 The speed of the missile shall be measured on the trailing edge of the m

20、issile after it exits the barrel. The photoelectricsensors can be mounted on an extension of the barrel or supported independently of the cannon. In either case the missile shallnot be accelerating as its trailing edge passes between the photoelectric sensors.X1.3 Bungee Test Apparatus:X1.3.1 Sugges

21、ted Components:X1.3.1.1 A rigid PVC (or other suitable) pipe having a 100-mm (4-in.) nominal inside diameter and a minimum length of 2.75m.E1886 13a7X1.3.1.2 Three to five 7.62-m lengths of 10-mm outside diameter 5-mm inside diameter latex rubber surgical tubing bandedtogether.X1.3.1.3 One 50 100 15

22、0-mm wood block with threaded eye hook mounted to and projecting from either 100 150-mm face.X1.3.1.4 Two through-beam photoelectric sensors of the same make and model with accuracy tolerances no greater than 62 %.X1.3.1.5 Mounting frame of general construction capable of supporting pipe and timing

23、and timing system without movementduring test.X1.3.1.6 One 3-m steel cable with a quick release snap hook attached to one end.X1.3.1.7 Hand operated cable winch with ratchet lock.X1.3.2 Assembly:X1.3.2.1 Assembly described is illustrated in Fig. X1.1.X1.3.2.2 Drill two holes through each side of the

24、 PVC pipe 610 mm and 1520 mm from one end of the pipe, respectively. Holesshould be of sufficient size to allow the light beams from the photoelectric sensors to pass through the holes unobstructed acrossthe diameter of the pipe.X1.3.2.3 Mount the photoelectric sensors on the pipe such that the ligh

25、t beams pass through the respective holes from one sideof the pipe to the other across the pipes diameter.X1.3.2.4 Drill one hole through each side of the PVC pipe approximately 150 mm from the end of the pipe upon which the sensorsare mounted. These holes should be located 90 around the pipe circum

26、ference from the holes described in X1.3.2.2.X1.3.2.5 Thread each end of the surgical tubing bundle through one of the respective holes described in X1.3.2.4 and fix the endssuch that they cannot pull out. Pull the center of the bundle through the pipe such that it exits the pipe at the opposite end

27、.FIG. X1.1 Bungee Test ApparatusE1886 13a8X1.3.2.6 Attach the wood block to the surgical tubing bundle such that the center of the block is aligned with the center of thebundle. The 100 150-mm face of the block with the eye hook protruding from it should face away from the end of the tube fromwhich

28、the tubing bundle exits.X1.3.2.7 Mount the tube/surgical tubing assembly to the frame as illustrated in Fig. X1.1.X1.3.2.8 Mount the hand winch to the frame in the illustrated location. Fix the end of the steel cable that does not have the quickrelease snap hook to the winch and wrap the cable aroun

29、d the drum of the winch. The end of the cable with the snap hook shouldhang free.X1.3.2.9 Connect the quick release snap hook to the eye hook of the wood block and draw enough cable on the winch drum toplace a slight tension in the surgical tubing bundle.X1.3.3 Operation:X1.3.3.1 Place the large mis

30、sile in the pipe such that the non-impacting end of the missile rests on the wood block of the surgicaltubing bundle.X1.3.3.2 Crank the hand winch to draw wood block back to place tension in the surgical tubing bundle. The amount of tensionplaced in the bundle is based on the number of tubes in the

31、bundle and the required missile propulsion speed.X1.3.3.3 Reposition the missile such that the end is centered on the wood block.X1.3.3.4 Setup and zero timing system for speed measurement.X1.3.3.5 Align pipe such that the projected missile will impact the test specimen at the specified location.X1.

32、3.3.6 Release retaining pin of the quick release snap hook to release wood block and propel missile.X1.4 Small Missile CannonA compressed air cannon shall be used that is capable of propelling missiles of the speed and sizedefined in 6.2.7.1. The cannon assembly shall be comprised of a compressed ai

33、r supply, a remote firing device and valve, a barrel,and a timing system. The small missile cannon shall be mounted on a frame designed to permit movement of the cannon so thatit can propel missiles to impact the test specimen at specified locations. The photoelectric sensors shall be positioned to

34、measuremissile speed within 150 cm of the impact point on the test specimen.X2. SPEED MEASURING SYSTEMSX2.1 For those wishing to use speed measuring devices that have already been developed, the following three systems arerecommended.NOTE X2.1These do not require special design; other systems are po

35、ssible.X2.2 Photoelectric SensorsTwo photoelectric sensors shall be used. Both photoelectric sensors shall be the same model. Anelectronic timing device shall be activated when the reference point of the missile passes the first sensor. The electronic timingdevice shall be stopped when the reference

36、 point of the missile passes the second sensor. The electronic timing device shall havean operating frequency of no less than 10 kHz with a response time not to exceed 0.15 ms. The speed of the missile shall bedetermined by dividing the distance between the two through-beam photoelectric sensors by

37、the time interval counted by theelectronic timing device.X2.3 High Speed Video CameraAhigh speed video camera and a single frame viewing device as specified in 9.1.2 may be usedas the speed measuring system in lieu of the speed measuring system described in X2.2. The high speed video camera shall be

38、 usedin conjunction with an appropriate grid that may be fixed background or on the missile, and a reference line that may be the trailingedge of the missile or a fixed background, respectively. The video camera shall be used to record the relative distance traveledbetween the line and the grid. The

39、 speed of the missile is computed as the product of the distance traveled in two consecutiveframes and the frame rate of the high speed video camera. For example, if the frame rate of the high speed video camera is 500E1886 13a9frames per second and the recorded change in position is 27 mm, then the

40、 missile speed is 500 0.027 = 13.5 m/s.X2.4 Standard Video CameraA standard video camera and a four head videotape playback device with stop action capabilitiesmay be used. The time between consecutive images is 130 s.X3. TESTING GLAZING PANELSX3.1 For those wishing to use the apparatus and procedur

41、es specified in this test method to test glazing materials, the followingprocedure is recommended.X3.2 Terminology:X3.2.1 Glazing panelThe transparent or translucent portion of the fenestration assembly which shall be comprised of glass,wired glass, laminated glass, glass/plastic laminates, plastic

42、sheet, or insulating glass.X3.2.2 Glazing materialThe material used to make a glazing panel.X3.3 Procedure:X3.3.1 This test procedure shall be conducted on glazing panel specimens that are used in windows, doors, curtain walls, or otherfenestration products.X3.3.2 Standard Test FrameThe standard tes

43、t frame shall be capable of supporting a rectangular glazing panel in a verticalplane. The standard test frame shall conform to Test Method E997.X3.3.3 Glazing panels shall be mounted in the test frame in accordance with Test Method E997.X3.3.4 Glazing panels mounted in the standard test frame shall

44、 be tested using the procedures outlined in this test method.REFERENCES(1) Mehta, K. C., Marshall, R. D., and Perry, D. C., Guide to the Use of the Wind Load Provisions of ASCE 7-88 (formerly ANSI A58.1), ASCE, NewYork, 1991.(2) Mehta, K. C., Minor, J. E., and Reinhold, T. A. ,“Wind Speed-Damage Cor

45、relation in Hurricane Frederick,” Journal of Structural Engineering , Vol109, No. 1, 1983, pp. 3749.(3) Minor, J. E., “How to Prepare Glass Buildings for Hurricanes,” Glass Digest, 1984 pp. 6064.(4) Minor, J. E., and Beason, W. L., “Window Glass Failures in Windstorms,” Journal of the Structural Div

46、ision, ASCE, Vol 102, No. ST1, 1976, pp.147160.(5) Minor, J. E., Beason, W. L., and Harris, P. L., “Designing for Windborne Missiles in Urban Areas,” Journal of the Structural Division, ASCE, Vol104, No. ST11, 1978, pp. 17491760.(6) NAHB Research Center, “Assessment of Damage to Single-Family Homes

47、Caused by Hurricanes Andrew and Iniki,” presented to U.S. Departmentof HUD, September 1993.(7) Walker, G. R., “Report on Cyclone TracyEffect on Buildings,” (3 Vol.), Dept. of Housing and Const.,Australian Government, Melbourne, Victoria,Australia.(8) Letchford, C. W., and Norville, H. S., “Wind Pres

48、sure Loading Cycles for Glazing During Hurricanes,” Journal of Wind Engineering and IndustrialAerodynamics, Vol 53, 1994, pp. 189206.(9) Twisdale, L. A., Vickery, P. J., and Steckley, A. C., “Analysis of Hurricane Windborne Debris Impact Risk for Residential Structures,” AppliedResearch Associates,

49、Inc., Raleigh, North Carolina, March 1996.E1886 13a10(10) Jancauskas, E. D., et al, “Computer Simulation of the Fatigue Behavior of Roof Cladding During the Passage of a Tropical Cyclone,” Proc. 12thAustralian Conference on the Mech. of Structures and Materials , Queensland University of Technology, 1990, pp. 327334.(11) Mahendran, M., “Towards anAppropriate Fatigue Loading for Roof Claddings in Cyclonic ProneAreas,” Physical Infrastructure Centre, QueenslandUniversity of Technology, School of Civil Engineering, Brisbane, Queensland, Austr