Designation: E 1886 – 97 An American National Standard

Standard Test Method for

Performance of Exterior Windows, Curtain Walls, Doors, and
Storm Shutters Impacted by Missile(s) and Exposed to
Cyclic Pressure Differentials1
This standard is issued under the fixed designation E 1886; 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 (e) indicates an editorial change since the last revision or reapproval.

1. Scope Windows, Curtain Walls, and Doors by Cyclic Static Air

1.1 This test method determines the performance of exterior Pressure Differential2
windows, curtain walls, doors, and storm shutters impacted by 2.2 ANSI/ASCE Standard:
missile(s) and subsequently subjected to cyclic static pressure ANSI/ASCE 7, American Society of Civil Engineers Min-
differentials. A missile propulsion device, an air pressure imum Design Loads for Buildings and Other Structures3
system, and a test chamber are used to model some conditions 2.3 American Lumber Standard:
which may be representative of windborne debris and pressures Document PS20-94—American Softwood Lumber Stan-
in a windstorm environment. This test method is applicable to dard4
the design of entire fenestration or shutter assemblies and their 3. Terminology
installation. The performance determined by this test method
relates to the ability of elements of the building envelope to 3.1 Definitions: General terms used in this test method are
remain unbreached during a windstorm. defined in Terminology E 631.
1.2 The specifying authority shall define the representative 3.2 Definitions of Terms Specific to This Standard:
conditions (see 10.1). 3.2.1 2 3 4 in. lumber—a dressed piece of surface dry,
1.3 The values stated in SI units are to be regarded as the softwood lumber as defined in Document PS20-94.
standard. Values given in parentheses are for information only. 3.2.2 air pressure cycle—beginning at a specified air pres-
Certain values contained in reference documents cited herein sure differential, the application of positive (negative) pressure
may be stated in inch-pound units and must be converted by the to achieve another specified air pressure differential and
user. returning to the initial specified air pressure differential.
1.4 This standard does not purport to address all of the 3.2.3 air pressure differential—the specified differential in
safety concerns, if any, associated with its use. It is the static air pressure across the specimen, creating an inward
responsibility of the user of this standard to establish appro- (outward) load, expressed in Pa (lb/ft2). The maximum air
priate safety and health practices and determine the applica- pressure differential (P) is specified or is equal to the design
bility of regulatory limitations prior to use. Specific hazard pressure.
statements are given in Section 7. 3.2.4 basic wind speed—the wind speed as determined by
the specifying authority.
2. Referenced Documents 3.2.5 design pressure—the uniform static air pressure dif-
2.1 ASTM Standards: ference, inward or outward, for which the test specimen would
E 330 Test Method for Structural Performance of Exterior be designed under service load conditions using conventional
Windows, Curtain Walls, and Doors by Uniform Static Air structural engineering specifications and concepts. This pres-
Pressure Difference2 sure is determined by either analytical or wind tunnel proce-
E 631 Terminology of Building Constructions2 dures (such as are specified in ANSI/ASCE 7).
E 997 Test Method for Structural Performance of Glass in 3.2.6 fenestration assembly—the construction intended to
Exterior Windows, Curtain Walls, and Doors Under the be installed to fill a wall or roof opening.
Influence of Uniform Static Loads by Destructive Meth- 3.2.7 missile—the object which is propelled toward a test
ods2 specimen.
E 1233 Test Method for Structural Performance of Exterior 3.2.8 positive (negative) cyclic test load—the specified
difference in static air pressure, creating an inward (outward)

1
This test method is under the jurisdiction of ASTM Committee E-6 on
3
Performance of Buildings and is the direct responsibility of Subcommittee E06.51 Available from the American Society of Civil Engineers, 1801 Alexander Bell
on Component Performance of Windows, Curtain Walls, and Doors. Drive, Reston, VA 20191-4400.
4
Current edition approved May 10, 1997. Published July 1997. Available from the American Lumber Standard Committee, Inc., P.O. Box 210,
2
Annual Book of ASTM Standards, Vol 04.11. Germantown, MD 20875.

Copyright © ASTM, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959, United States.

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 E 1886
loading, for which the specimen is to be tested under repeated 5.1.2 Windows, doors, and curtain walls are building enve-
conditions, expressed in Pa (lb/ft2). lope components often subject to damage in windstorms. The
3.2.9 shutter assembly—the construction intended to be damage caused by windborne debris during windstorms goes
installed in front of fenestration assemblies to provide protec- beyond failure of building envelope components such as
tion. windows, doors, and curtain walls. Breaching of the envelope
3.2.10 specifying authority—the entity responsible for de- exposes a building’s contents to the damaging effects of
termining and furnishing information required to perform this continued wind and rain (1, 4-7). A potentially more serious
test method. result is internal pressurization. When the windward wall of a
3.2.11 test loading program—the entire sequence of air building is breached, the internal pressure in the building
pressure cycles to be applied to the test specimen. increases, resulting in increased outward acting pressure on the
3.2.12 test specimen—the entire assembled unit submitted other walls and the roof. The internal pressure coefficient (see
for test. ANSI/ASCE 7), which is one of several design parameters, can
3.2.13 windborne debris—objects carried by the wind in increase by a factor as high as four. This can increase the net
windstorms. outward acting pressure by a factor as high as two.
3.2.14 windstorm—a weather event, such as a hurricane, 5.1.3 The commentary to ANSI/ASCE 7-93 discusses inter-
with high sustained winds and turbulent gusts capable of nal pressure coefficients and the increased value to be used in
generating windborne debris. designing envelopes with “openings” as follows:
“Openings” in Table 9 (Internal Pressure Coefficients for Buildings) means
4. Summary of Test Method permanent or other openings that are likely to be breached during high
4.1 This test method consists of mounting the test specimen, winds. For example, if window glass is likely to be broken by missiles dur-
ing a windstorm, this is considered to be an opening. However, if doors
impacting the test specimen with a missile(s), and then and windows and their supports are designed to resist specified loads and
applying cyclic static pressure differentials across the test the glass is protected by a screen or barrier, they need not be considered
specimen in accordance with a specified test loading program, openings. (109)

observing and measuring the condition of the test specimen, Thus, there are two options in designing buildings for
and reporting the results. windstorms with windborne debris: buildings designed with
“openings” (partially enclosed buildings) to withstand the
5. Significance and Use
higher pressures noted in the commentary to ANSI/ASCE 7-93
5.1 Structural design of exterior windows, curtain walls, and, alternatively, building envelope components designed so
doors, and storm shutters is typically based on positive and they are not likely to be breached in a windstorm when
negative design pressure(s). Design pressures based on wind impacted by windborne debris. The latter approach reduces the
speeds with a mean recurrence interval (usually 25–100 years) likelihood of exposing the building contents to the weather.
that relates to desired levels of structural reliability and are 5.2 In this test method, a test specimen is first subjected to
appropriate for the type and importance of the building (1).5 specified missile impact(s) followed by the application of a
The adequacy of the structural design is substantiated by other specified number of cycles of positive and negative static
test methods such as Test Methods E 330 and E 1233 which pressure differential (8). The assembly must satisfy the pass/
discuss proof loads as added factors of safety. However, these fail criteria established by the specifying authority, which may
test methods do not account for other factors such as impact allow damage such as deformation, deflection, or glass break-
from windborne debris followed by fluctuating pressures age.
associated with a severe windstorm environment. As demon-
strated by windstorm damage investigations, windborne debris 5.3 The windborne debris generated during a severe wind-
is present in hurricanes and has caused a significant amount of storm varies greatly, depending upon windspeed, height above
damage to building envelopes (2-7). The actual in-service the ground, terrain, surrounding structures, and other sources
performance of fenestration assemblies and storm shutters in of debris (4). Typical debris in hurricanes consists of missiles
areas prone to severe windstorms is dependent on many including, but not limited to, roof gravel, roof tiles, signage,
factors. Windstorm damage investigations have shown that the portions of damaged structures, framing lumber, roofing ma-
effects of windborne debris, followed by the effects of repeated terials, and sheet metal (4,7,9). Median impact velocities for
or cyclic wind loading, were a major factor in building damage missiles affecting residential structures considered in Ref (7)
(2-7). ranged from 9 m/s (30 fps) to 30 m/s (100 fps). The missiles
5.1.1 Many factors affect the actual loading on building and their associated velocity ranges used in this test method are
surfaces during a severe windstorm, including varying wind selected to reasonably represent typical debris produced by
direction, duration of the wind event, height above ground, windstorms.
building shape, terrain, surrounding structures, and other fac- 5.4 To determine design wind loads, averaged wind speeds
tors (1). The resistance of fenestration or shutter assemblies to are translated into air pressure differences. Superimposed on
wind loading after impact depends upon product design, the averaged winds are gusts whose aggregation, for short
installation, load magnitude, duration, and repetition. periods of time (ranging from fractions of seconds to a few
seconds) may move at considerably higher speeds than the
averaged winds. Wind pressures related to building design,
5
The boldface numbers in parentheses refer to the list of references at the end of wind intensity versus duration, frequency of occurrence, and
this standard. other factors are considered.

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5.4.1 Wind speeds are typically selected for particular and with a response time less than 50 ms. Examples of
geographic locations and probabilities of occurrence from wind acceptable apparatus are: mechanical pressure gages and elec-
speed maps such as those prepared by the National Weather tronic pressure transducers.
Service, from appropriate wind load documents such as ANSI/ 6.2.5 Missile Propulsion Device(s)—Any device capable of
ASCE 7 or from building codes enforced in a particular propelling the missile at a specified speed, orientation, and
geographic region. impact location. The missile shall not be accelerating upon
5.4.2 Equivalent static pressure differences are calculated impact due to the force of gravity along a line normal to the
using the selected wind speeds (1). specimen. Examples of commonly used missile propulsion
5.5 Cyclic pressure effects on fenestration assemblies after devices are found in Appendix X1.
impact by windborne debris are significant (6-8, 10-12). It is 6.2.6 Speed Measuring System—A system capable of mea-
appropriate to test the strength of the assembly for a time suring missile speeds within the tolerances defined in 11.2.1.
duration representative of sustained winds and gusts in a Typical speed measuring systems are described in Appendix
windstorm. Gust wind loads are of relatively short duration. X2.
Other test methods, such as Test Methods E 330 and E 1233, 6.2.7 Missile—Missiles shall be one or more of the follow-
do not model gust loadings. They are not to be specified for the ing:
purpose of testing the adequacy of the assembly to remain 6.2.7.1 Small Missile—A solid steel ball having a mass of 2
unbreached in a windstorm environment following impact by g (0.004 lb) 6 5 %, with an 8-mm (5⁄16-in.) nominal diameter,
windborne debris. and an impact speed between 0.40 and 0.75 of the basic wind
5.6 Further information on the subjects covered in Section 5 speed (3-s gust in accordance with ANSI/ASCE 7).
is available in Refs (1-12). 6.2.7.2 Large Missile—A No. 2 or better Southern Yellow
Pine or Douglas Fir 2 3 4 in. lumber having an American
6. Apparatus Lumber Standard Committee accredited agency mark having a
6.1 Use any equipment capable of performing the test mass of between 2050 g 6 100 g (4.5 6 0.25 lb) and 6800 g
procedure within the allowable tolerances. 6 100 g (15.0 6 0.25 lb) and having a length between 1.2 m
6.2 Major Components: 6 100 mm (4 ft 6 4 in.) and 4.0 m 6 100 mm (13.2 ft 6 4 in.)
6.2.1 Mounting Frame—The fixture which supports the test and an impact speed between 0.10 and 0.55 of the basic wind
specimen in a vertical position during testing. The maximum speed (3-s gust in accordance with ANSI/ASCE 7). The missile
deflection of the longest member of the mounting frame either shall have no defects, including knots, splits, checks, shakes, or
during impact or the maximum specified static air pressure wane within 30 cm (12 in.) of the impact end. The impact end
differential shall not exceed L/360, where L denotes the longest shall be trimmed square in accordance with the rules certified
unsupported length of a member of the mounting frame. by the American Lumber Standard Committee. If required for
Deflection measurements shall be made normal to the plane of propulsion, a circular sabot having a mass of no more than 200
the specimen at the point of maximum deflection. The mount- g (0.5 lb) may be applied to the trailing edge of the large
ing frame shall be either integral with the test chamber or missile. The mass and length of the large missile includes the
capable of being installed into the test chamber prior to or mass and length of the sabot.
following missile impact(s). The mounting frame must be 6.2.7.3 Other Missile—Any other representative missile
anchored so it does not move when the specimen is impacted. with mass, size, shape, and impact speed as a function of basic
6.2.2 Air Pressure Cycling Test Chamber—An enclosure or wind speed determined by engineering analysis such as Ref
box with an opening against which the test specimen is (9).
installed. It must be capable of withstanding the specified
7. Hazards
cyclic static pressure differential. Pressure taps shall be pro-
vided to facilitate measurement of the cyclic static pressure 7.1 This test method involves potentially hazardous situa-
differential. They shall be located such that the measurements tions. Proper precautions shall be taken to protect all personnel.
are unaffected by air supplied to or evacuated from the test 7.2 All observers shall be isolated from the path of the
chamber or by any other air movements. missile during the missile impact portion of the test.
6.2.3 Air Pressure System—A controllable blower, a com- 7.3 Keep observers at a safe distance from the test specimen
pressed air supply/vacuum system, or other suitable system during the entire procedure.
capable of providing the required maximum air pressure 8. Test Specimens
differential (inward and outward acting) across the test speci- 8.1 The test specimen shall consist of the entire fenestration
men. Specified pressure differentials across the test specimen or shutter assembly and contain all devices used to resist wind
shall be imposed and controlled through any system that and windborne debris. Test specimens for large fenestration
subjects the test specimen to the prescribed test loading and curtain wall assemblies shall be one panel unless otherwise
program. Examples of suitable control systems include manu- specified.
ally operated valves, electrically operated valves, or computer 8.2 All parts of the test specimen shall be full size, as
controlled servo-valves. specified for actual use, using the identical materials, details,
6.2.4 Air Pressure Measuring Apparatus—Pressure differ- and methods of construction.
entials across the test specimen shall be measured by an air
pressure measuring apparatus with an accuracy of 62 % of its 9. Calibration
maximum rated capacity, or 6100 Pa (2 psf), whichever is less, 9.1 The speed measuring system shall be calibrated to an

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accuracy of 62 % of the elapsed time required to measure the the test specimen with the same number of equivalent fasteners
speed of the specified missile. Calibration shall be performed at located in the same manner as the intended installation. This
the manufacturers specified interval, but in any event, not more test shall not be used to evaluate anchorage of curtain wall and
than six months prior to the test date. The speed measuring heavy commercial assemblies. In those cases, the specimen
system shall be calibrated by at least one of the following shall be securely anchored to facilitate testing. The test
methods: specimen shall not be removed from the mounting frame at any
9.1.1 Photographically, using a stroboscope and a still time during the test sequence.
camera, 11.1.1 Unless otherwise specified, separate and condition
9.1.2 Photographically, using a high speed motion picture or the specimens for at least 4 h within a temperature range of
video camera with a frame rate exceeding 500 frames per 15°C to 35°C (59°F to 95°F).
second and capable of producing a clear image and a device 11.1.2 Missile Impact—Secure the specimen and mounting
that allows single frame viewing, frame such that the missile will impact the exterior side of the
9.1.3 Using gravity to accelerate a free-falling object having specimen as installed.
negligible air drag through the timing system and comparing 11.1.3 Locate the end of the propulsion device from which
measured and theoretical elapsed times, or the missile will exit at a minimum distance from the specimen
9.1.4 Using any independently calibrated speed measuring equal to 1.5 times the length of the missile. This distance shall
system with an accuracy of 61 %. be no less than 1.80 m.
9.2 Electronic pressure transducers shall be calibrated at 6 11.1.4 Set up appropriate signal/warning devices to prevent
month intervals using a NIST traceable calibrating system or a test or other personnel, or both, from coming between the
manometer readable to 2.5 Pa. propulsion device and the test specimen during testing.
9.3 Calibration of manometers is normally not required 11.1.5 Weigh each missile within 15 min prior to impact.
provided the instruments are used at a temperature near their 11.1.6 Load the missile into propulsion device.
design temperature. 11.1.7 Reset the speed measuring system.
11.1.8 Align the missile propulsion device such that the
10. Required Information specified missile will impact the test specimen at the specified
10.1 The specifying authority shall supply the following location.
information and requirements: 11.2 Propel the missile at the specified impact speed and
10.1.1 Number of test specimens, location.
10.1.1.1 Conditioning temperature of specimens, 11.2.1 The measured missile speed will be within the
10.1.2 Pass/fail criteria, following respective tolerances at any point after the missile
10.1.3 Basic wind speed, acceleration caused by the propulsion device equals zero:
10.1.4 Missile, 62 % specified speed when speed #23 m/s
10.1.4.1 Description of the missile, including dimensions, 61 % specified speed when speed >23 m/s
mass, and tolerances, 11.2.2 For missiles having a longitudinal axis, on impact the
10.1.4.2 Missile speed at impact, or the equation relating longitudinal axis of the missile shall be within 65° of a line
missile speed to basic wind speed, normal to the specimen at the specified impact point.
10.1.4.3 Missile orientation at impact,
10.1.4.4 Number of impacts, and NOTE 1—From a horizontal datum, measure the vertical height to the
10.1.4.5 Location of impacts on the test specimens and center of the exit end of the propulsion device (if it is horizontal), hB, and
the vertical height to the center of the missile impact point on the
tolerances.
specimen, hI. To ensure the missile rotates less than 5° prior to impact:
10.1.5 Test loading program, and
10.1.5.1 The maximum air pressure differential and its
relationship to the design pressure,
5° # tan21 Uh 2d h U
B I
(1)
where d denotes horizontal distance from the exit end of the propulsion
10.1.5.2 The positive and negative cyclic test loads,
device to the specimen.
10.1.5.3 The number of cycles of cyclic test load sequence
to be applied, and 11.3 If required, repeat steps 11.1.4-11.2 at all additional
10.1.5.4 The minimum and maximum duration for each impact locations specified for the specimen.
cycle. 11.4 Air Pressure Cycling—If the mounting frame is not
10.1.6 Whether or not certification of the calibration is integral within the test chamber, attach the mounting frame to
required. the test chamber such that the exterior side of the test specimen
faces outward from the chamber.
11. Test Procedure 11.4.1 If at any time during testing the specified maximum
11.1 Preparation—Remove from the test specimen any pressure differential cannot be achieved in either direction due
sealing or construction material that is not intended to be used to excessive air leakage, cover all cracks and joints through
when the unit is installed in or on a building. Support and which leakage occurs with tape or film in such manner as to
secure the test specimen into the mounting frame in a vertical stop the leakage. Tape shall not be used when there is a
position using the same number and type of anchors normally probability that it will restrict significantly differential move-
used for product installation as defined by the manufacturer or ment between adjoining segments of the specimen, in which
as required for a specific project. If this is impractical, install case cover both sides of the test specimen with a single

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thickness of polyethylene or other plastic film no thicker than 12.1.5.1 Any deviation from the drawings or any modifica-
0.050 mm (0.002 in.). The technique of application is impor- tions made to the test specimen to obtain the reported values
tant in order that the full load is permitted to be transferred to shall be noted on the drawings and in the report.
the test specimen and that the film does not prevent movement 12.1.6 When the tests are made to check conformity of the
or failure of the test specimen. Apply the film loosely with test specimen to a particular specification or pass/fail criteria,
extra folds of material at each corner and at all offsets and an identification or description of that specification or criteria,
recesses. When the load is applied there shall be no fillet 12.1.7 Results for each test specimen,
caused by tightness of the plastic film. 12.1.8 Impact test,
11.4.2 Unless otherwise specified, apply the cyclic static 12.1.8.1 The location of impact(s) on each test specimen,
pressure differential loading in accordance with Table 1 in 12.1.8.2 The exact description of the missile including
which P denotes the maximum inward (positive) and outward dimensions and mass (weight),
(negative) air pressure differentials as defined in 3.2.3. 12.1.8.3 The missile speed and orientation at impact, and
11.4.2.1 Unless otherwise specified, the duration of each air 12.1.8.4 The conditioning temperature of the specimens.
pressure cycle shall not be less than 1 s and not more than 5 s. 12.1.9 Cyclic pressure test,
Dwell time between successive cycles shall be no more than 1 12.1.9.1 The cyclic static pressure loading differential and
s. sequence,
11.4.2.2 Interruptions for equipment maintenance and repair 12.1.9.2 The maximum air pressure differential (P) and its
shall be permitted. relationship to the design pressure, and
11.4.2.3 The test specimen shall not contact any portion of 12.1.9.3 A statement as to whether or not tape or film, or
the test chamber at any time during the application of the cyclic both, were used to seal against air leakage and whether in the
static pressure differential loading. judgment of the test engineer the tape or film influenced the
results of the test.
12. Report
12.1.10 A description of the condition of the test specimens
12.1 Report the following information: after completion of each portion of testing, including details of
12.1.1 Date of test and report, damage and any other pertinent observations,
12.1.2 Names and addresses of the testing agency that 12.1.11 A statement that the tests were conducted in accor-
conducted the tests and the requester of the tests, dance with this test method,
12.1.3 Manufacturer’s model number or any other method 12.1.12 A statement of whether, upon completion of testing,
of identification, the test specimens pass or fail in accordance with any specified
12.1.4 A description of the test specimen, including all parts criteria,
and components, glazing thickness and construction, and the 12.1.13 The name(s) of individual(s) conducting the test
number of specimens tested, and the author of the report,
12.1.5 Detailed drawings of the test specimen, showing 12.1.14 Signatures of persons responsible for supervision of
dimensioned section profiles, sash or door dimensions and the tests and a list of all observers, and
arrangement, framing location, panel arrangement, installation 12.1.15 Any additional data or information considered to be
and spacing of anchorage, weather-stripping, locking arrange- useful to a better understanding of the test results, conclusions,
ment, hardware, sealants, glazing details, test specimen sealing or recommendations. (Append to report.)
methods, and any other pertinent construction details,
13. Precision and Bias
TABLE 1 Cyclic Static Pressure Differential Loading
Loading Loading Air Pressure Number of Air
13.1 Due to the lack of sufficient test data, the precision and
Sequence Direction Cycles Pressure Cycles bias of this test method cannot be determined at this time.
1 Positive 0.2P–0.5P 3500 Similar test methods have been performed by several labora-
2 Positive 0.0P–0.6P 300 tories, however, there are differences between tests currently
3 Positive 0.5P–0.8P 600 being performed and this test method.
4 Positive 0.3P–1.0P 100
5 Negative 0.3P–1.0P 50
6 Negative 0.5P–0.8P 1050 14. Keywords
7 Negative 0.0P–0.6P 50
8 Negative 0.2P–0.5P 3350 14.1 cyclic pressure loading; fenestration; hurricanes; mis-
sile impact; storm shutters; windborne debris; windstorms

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APPENDIXES

(Nonmandatory Information)

X1. MISSLE PROPULSION DEVICES

X1.1 For those wishing to use missile propulsion devices the missile shall not be accelerating as its trailing edge passes
which have already been developed to launch certain types of between the photoelectric sensors.
missiles, the following apparatus are recommended:
X1.3 Bungee Test Apparatus
X1.2 Large Missile Air Cannon—The large missile air X1.3.1 Suggested Components:
cannon shall use compressed air to propel the large missile. X1.3.1.1 A rigid PVC (or other suitable) pipe having a
The cannon shall be capable of producing missile impact at the 100-mm (4-in.) nominal inside diameter and a minimum length
speeds defined in 6.2.7.2. The large missile cannon shall of 2.75 m.
consist of four major components: a compressed air supply, a X1.3.1.2 Three to five 7.62-m lengths of 10-mm outside
pressure release valve, a barrel and support frame, and a speed diameter 3 5-mm inside diameter latex rubber surgical tubing
measuring system for determining the missile speed. banded together.
X1.2.1 The barrel of the large missile cannon shall consist X1.3.1.3 One 50 3 100 3 150-mm wood block with
of a 100-mm (4-in.) nominal inside diameter pipe and shall threaded eye hook mounted to and projecting from either
have a length at least as long as the missile. The total length of 100 3 150-mm face.
the barrel shall be the distance from the pressure valve to the X1.3.1.4 Two through-beam photoelectric sensors of the
vent holes in advance of the timing system or to the mouth of same make and model with accuracy tolerances no greater than
the barrel. The barrel of the large missile cannon shall be 62 %.
mounted on a support frame in a manner to facilitate aiming the X1.3.1.5 Mounting frame of general construction capable of
missile so that it impacts the specimen at the desired location. supporting pipe and timing and timing system without move-
X1.2.2 The large missile is defined in 6.2.7.2. The end of the ment during test.
missile that impacts the target is denoted as the missile’s X1.3.1.6 One 3-m steel cable with a quick release snap hook
impact end. The end of the missile opposite to the impact end attached to one end.
is denoted as the missile’s trailing edge. A sabot shall be used X1.3.1.7 Hand operated cable winch with ratchet lock.
at the trailing edge of the missile to facilitate launching. X1.3.2 Assembly:
X1.2.3 The speed of the missile shall be measured on the X1.3.2.1 Assembly described is illustrated in Fig. X1.1.
trailing edge of the missile after it exits the barrel. The X1.3.2.2 Drill two holes through each side of the PVC pipe
photoelectric sensors can be mounted on an extension of the 610 mm and 1520 mm from one end of the pipe, respectively.
barrel or supported independently of the cannon. In either case Holes should be of sufficient size to allow the light beams from

FIG. X1.1 Bungee Test Apparatus

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the photoelectric sensors to pass through the holes unob- X1.3.3 Operation:
structed across the diameter of the pipe. X1.3.3.1 Place the large missile in the pipe such that the
X1.3.2.3 Mount the photoelectric sensors on the pipe such non-impacting end of the missile rests on the wood block of the
that the light beams pass through the respective holes from one surgical tubing bundle.
side of the pipe to the other across the pipe’s diameter.
X1.3.3.2 Crank the hand winch to draw wood block back to
X1.3.2.4 Drill one hole through each side of the PVC pipe
place tension in the surgical tubing bundle. The amount of
approximately 150 mm from the end of the pipe upon which
the sensors are mounted. These holes should be located 90° tension placed in the bundle is based on the number of tubes in
around the pipe circumference from the holes described in the bundle and the required missile propulsion speed.
X1.3.2.2. X1.3.3.3 Reposition the missile such that the end is centered
X1.3.2.5 Thread each end of the surgical tubing bundle on the wood block.
through one of the respective holes described in X1.3.2.4 and X1.3.3.4 Setup and zero timing system for speed measure-
fix the ends such that they cannot pull out. Pull the center of the ment.
bundle through the pipe such that it exits the pipe at the X1.3.3.5 Align pipe such that the projected missile will
opposite end. impact the test specimen at the specified location.
X1.3.2.6 Attach the wood block to the surgical tubing
bundle such that the center of the block is aligned with the X1.3.3.6 Release retaining pin of the quick release snap
center of the bundle. The 100 3 150-mm face of the block with hook to release wood block and propel missile.
the eye hook protruding from it should face away from the end
of the tube from which the tubing bundle exits. X1.4 Small Missile Cannon—A compressed air cannon
X1.3.2.7 Mount the tube/surgical tubing assembly to the shall be used that is capable of propelling missiles of the speed
frame as illustrated in Fig. X1.1. and size defined in 6.2.7.1. The cannon assembly shall be
X1.3.2.8 Mount the hand winch to the frame in the illus- comprised of a compressed air supply, a remote firing device
trated location. Fix the end of the steel cable that does not have and valve, a barrel, and a timing system. The small missile
the quick release snap hook to the winch and wrap the cable cannon shall be mounted on a frame designed to permit
around the drum of the winch. The end of the cable with the movement of the cannon so that it can propel missiles to impact
snap hook should hang free. the test specimen at specified locations. The photoelectric
X1.3.2.9 Connect the quick release snap hook to the eye sensors shall be positioned to measure missile speed within 150
hook of the wood block and draw enough cable on the winch cm of the impact point on the test specimen.
drum to place a slight tension in the surgical tubing bundle.

X2. SPEED MEASURING SYSTEMS

X2.1 For those wishing to use speed measuring devices that may be used as the speed measuring system in lieu of the speed
have already been developed, the following three systems are measuring system described in X2.2. The high speed video
recommended. camera shall be used in conjunction with an appropriate grid
NOTE X2.1—These do not require special design; other systems are that may be fixed background or on the missile, and a reference
possible. line that may be the trailing edge of the missile or a fixed
background, respectively. The video camera shall be used to
X2.2 Photoelectric Sensors—Two photoelectric sensors record the relative distance traveled between the line and the
shall be used. Both photoelectric sensors shall be the same grid. The speed of the missile is computed as the product of the
model. An electronic timing device shall be activated when the distance traveled in two consecutive frames and the frame rate
reference point of the missile passes the first sensor. The of the high speed video camera. For example, if the frame rate
electronic timing device shall be stopped when the reference
of the high speed video camera is 500 frames per second and
point of the missile passes the second sensor. The electronic
the recorded change in position is 27 mm, then the missile
timing device shall have an operating frequency of no less than
speed is 500 3 0.027 5 13.5 m/s.
10 kHz with a response time not to exceed 0.15 ms. The speed
of the missile shall be determined by dividing the distance
between the two through-beam photoelectric sensors by the X2.4 Standard Video Camera—A standard video camera
time interval counted by the electronic timing device. and a four head videotape playback device with stop action
capabilities may be used. The time between consecutive
X2.3 High Speed Video Camera—A high speed video images is 1⁄30 s.
camera and a single frame viewing device as specified in 9.1.2

7
 E 1886

X3. TESTING GLAZING PANELS

X3.1 For those wishing to use the apparatus and procedures X3.3.1 This test procedure shall be conducted on glazing
specified in this test method to test glazing materials, the panel specimens that are used in windows, doors, curtain walls,
following procedure is recommended. or other fenestration products.
X3.3.2 Standard Test Frame—The standard test frame shall
X3.2 Terminology:
be capable of supporting a rectangular glazing panel in a
X3.2.1 Glazing panel—The transparent or translucent por- vertical plane. The standard test frame shall conform to Test
tion of the fenestration assembly which shall be comprised of Method E 997.
glass, wired glass, laminated glass, glass/plastic laminates,
X3.3.3 Glazing panels shall be mounted in the test frame in
plastic sheet, or insulating glass.
accordance with Test Method E 997.
X3.2.2 Glazing material—The material used to make a
glazing panel. X3.3.4 Glazing panels mounted in the standard test frame
shall be tested using the procedures outlined in this test
X3.3 Procedure: method.

REFERENCES

(1) Mehta, K. C., Marshall, R. D., and Perry, D. C., Guide to the Use of (8) Letchford, C. W., and Norville, H. S., “Wind Pressure Loading Cycles
the Wind Load Provisions of ASCE 7-88 (formerly ANSI A58.1), for Glazing During Hurricanes,” Journal of Wind Engineering and
ASCE, New York, 1991. Industrial Aerodynamics, Vol 53, 1994, pp. 189–206.
(2) Mehta, K. C., Minor, J. E., and Reinhold, T. A. ,“Wind Speed-Damage (9) Twisdale, L. A., Vickery, P. J., and Steckley, A. C., “Analysis of
Correlation in Hurricane Frederick,” Journal of Structural Engineer- Hurricane Windborne Debris Impact Risk for Residential Structures,”
ing, Vol 109, No. 1, 1983, pp. 37–49. Applied Research Associates, Inc., Raleigh, North Carolina, March
(3) Minor, J. E., “How to Prepare Glass Buildings for Hurricanes,” Glass 1996.
Digest, 1984 pp. 60–64.
(10) Jancauskas, E. D., et al, “Computer Simulation of the Fatigue
(4) Minor, J. E., and Beason, W. L., “Window Glass Failures in Wind-
Behavior of Roof Cladding During the Passage of a Tropical
storms,” Journal of the Structural Division, ASCE, Vol 102, No. ST1,
Cyclone,” Proc. 12th Australian Conference on the Mech. of Struc-
1976, pp. 147–160.
tures and Materials, Queensland University of Technology, 1990, pp.
(5) Minor, J. E., Beason, W. L., and Harris, P. L., “Designing for
327–334.
Windborne Missiles in Urban Areas,” Journal of the Structural
Division, ASCE, Vol 104, No. ST11, 1978, pp. 1749–1760. (11) Mahendran, M., “Towards an Appropriate Fatigue Loading for Roof
(6) NAHB Research Center,“ Assessment of Damage to Single-Family Claddings in Cyclonic Prone Areas,” Physical Infrastructure Centre,
Homes Caused by Hurricanes Andrew and Iniki,” presented to U.S. Queensland University of Technology, School of Civil Engineering,
Department of HUD, September 1993. Brisbane, Queensland, Australia, 1993.
(7) Walker, G. R., “Report on Cyclone Tracy—Effect on Buildings,” (3 (12) Technical Record 440, “Guidelines for Testing and Evaluation of
Vol.), Dept. of Housing and Const., Australian Government, Mel- Products for Cyclone-Prone Areas,” Department of Housing and
bourne, Victoria, Australia. Construction, Australian Government, Australia.

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