ASTM F330-89(2004)
(Test Method)Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures
Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures
SIGNIFICANCE AND USE
This test method may be used for: bird impact testing of aircraft crew compartment transparencies and supporting structure to verify the design; compilation of test data for use in verification of future transparency and supporting structure design and analytical methods; and comparative evaluation of materials.
SCOPE
1.1 This test method covers conducting bird impact tests under a standard set of conditions by firing a packaged bird at a stationary transparency mounted in a support structure.
1.2 The values stated in inch-pound units are to be regarded as the standard. The values given in parentheses are for information only.
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use. For specific hazard statements, see Section 8.
General Information
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Standards Content (Sample)
NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information.
Designation:F330–89(Reapproved2004)
Standard Test Method for
Bird Impact Testing of Aerospace Transparent Enclosures
ThisstandardisissuedunderthefixeddesignationF330;thenumberimmediatelyfollowingthedesignationindicatestheyearoforiginal
adoptionor,inthecaseofrevision,theyearoflastrevision.Anumberinparenthesesindicatestheyearoflastreapproval.Asuperscript
epsilon (´) indicates an editorial change since the last revision or reapproval.
This standard has been approved for use by agencies of the Department of Defense.
1. Scope 3.2.2 Bird velocity, and
3.2.3 Instrumentation.
1.1 This test method covers conducting bird impact tests
under a standard set of conditions by firing a packaged bird at
4. Significance and Use
a stationary transparency mounted in a support structure.
4.1 Thistestmethodmaybeusedfor:birdimpacttestingof
1.2 The values stated in inch-pound units are to be regarded
aircraftcrewcompartmenttransparenciesandsupportingstruc-
as the standard. The values given in parentheses are for
ture to verify the design; compilation of test data for use in
information only.
verification of future transparency and supporting structure
1.3 This standard does not purport to address all of the
design and analytical methods; and comparative evaluation of
safety concerns, if any, associated with its use. It is the
materials.
responsibility of the user of this standard to establish appro-
priate safety and health practices and determine the applica-
5. Apparatus
bility of regulatory limitations prior to use. For specific hazard
5.1 Gun, compressed gas, conforming in principle to Fig. 1,
statements, see Section 8.
comprising:
2. Terminology 5.1.1 Pressure Tank, of capacity and working pressure as
discussed in Note 1.
2.1 Definitions:
2.1.1 bird—thecarcassthatisusedtoimpactthetestarticle.
NOTE 1—Agun capable of propelling a 4-lb (1.81-kg) bird in excess of
2.1.2 bird package—the bird and container that encases the 650 knots (334 m/s) has a barrel 60 ft (18.3 m) long, bore of 6 in. (153
3 3
mm), and a pressure tank volume of 30 ft (0.849 m ) with an allowable
bird to prevent disintegration enroute to target.
working pressure of 250 psi (1.725 310 Pa).
2.1.3 gun—the device that propels the bird toward the
target. 5.1.2 Release Mechanism, comprised of a firing solenoid,
2.1.4 sabot—the container that is used to adapt the bird
diaphragm, and a cutter. Upon initiation of the firing sequence,
package to the gun barrel. the release mechanism allows the compressed gas stored in the
2.1.5 stripper—the device that stops the sabot at the end of
pressure tank to flow rapidly into the gun barrel and propel the
the gun barrel so that only the bird and package exits from the projectile.
barrel.
NOTE 2—The most common designs normally use either one or two
2.1.6 test article—the transparency and supporting struc-
diaphragms in the release mechanism. In the single diaphragm design, the
ture.
diaphragm is mechanically ruptured upon firing (see Fig. 1). In the dual
diaphragm system, pressurized gas between the two pressurized gas
3. Summary of Test Method
diaphragms is bled to initiate firing by allowing the stored gas to burst
each diaphragm in rapid succession.
3.1 This test method employs a smooth-bore bird gun that
fires a chicken carcass so that it impacts a stationary aerospace
5.1.3 Barrel (Launch Tube), a smooth bore tube that guides
transparency mounted in a supporting structure.
thepackagedbird(andsabotifused)duringitsaccelerationby
3.2 The specific parameters described by this test method
the expanding air from the pressure tank. The bore and length
are:
of the barrel is chosen both to accommodate the largest of the
3.2.1 Bird weight and condition,
projectiles to be used and for the overall performance require-
ments of the gun.
5.1.4 Sabot Stripper may be mounted at the end of the
This test method is under the jurisdiction of ASTM Committee F07 on
launcher tube. The purpose of the sabot stripper is to arrest or
Aerospace andAircraft and is the direct responsibility of Subcommittee F07.08 on
Transparent Enclosures and Materials. deflectthesabot,allowingonlythepackagedbirdtoimpactthe
Current edition approved Oct. 1, 2004. Published October 2004. Originally
test article.
approved in 1979. Last previous edition approved in 1999 as F330–89 (1999).
DOI: 10.1520/F0330-89R04.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
F330–89 (2004)
FIG. 1 Representative Air Gun
5.2 Velocity Measurement System: 5.4 Test Instrumentation:
5.2.1 The essential features of the velocity measurement
5.4.1 Weight Measurement—The weight scale shall have an
system are that it be accurate and repeatable, not be triggered
accuracy of at least 0.063 oz (1.8 g).
bysmallstrayobjectsthatmaybetravelingwiththeprojectile,
5.4.2 Mounting Angle Measurements (Pitch, Roll and
and not alter the flight path or damage the projectile.
Yaw)—The instrument for measuring the angle, at which the
5.2.2 Preferred velocity measurement systems use timing
test article or its support structure is mounted, shall have an
stations, located between the gun barrel and the test specimen, 1
accuracy of ⁄4 ° (0.00436 radian).
whicharetriggeredbytheprojectilesbreakageofamechanical
5.4.3 Temperature Measurement—The instrument system
link “break wire” or through the interruption of a light beam.
for measuring temperatures shall have an accuracy of 65°F
The velocity is then computed and averaged from the known
(2.8°C).
distances between the timing stations. Rapid sequence photog-
5.4.4 Velocity Measurement—The instrumentation used
raphy, in conjunction with a background gridwork, may be
with the velocity measurement system shall provide for an
used to provide a redundant system.
overall system accuracy within 62%.
NOTE 3—When using a light beam measuring system under high-
5.4.5 Rapid Sequence, at least one high-speed camera shall
humidity conditions, it is possible that the bird can become enveloped in
beusedtoproviderecordsofthebirdimpactingthetarget.The
acloudofwaterdropletsthatcouldcausetriggeringofthelightbeamsand
camera lighting conditions and controlling instrumentation
the bird package shown in the film might not be clear. When using a
shall be adjusted to provide a minimum of the following
“break wire” system, it is imperative that the tension of the wires be
camera frames per second at impact:
adjusted to within close tolerances in order to obtain consistent results.
F 51000 15 Vor (1)
5.3 Environmental Control:
5.3.1 The environmental control apparatus may be used to
F 51000 11.53 v (2)
heat or cool the test article to the desired temperature at the
time of impact. The environmental control required shall be
capableofprovidingthetemperaturerangesurroundingthetest
where:
article that would critically affect the physical properties of
F = exposure rate (frames per second),
aircraft transparencies. This range is normally−65°F (−54°C)
V = projectile velocity (ft/s), and
to 250°F (121°C). The facility shall be capable of providing
v = projectile velocity (m/s)
these temperatures for a sufficient time to achieve steady-state
Timing marks may be automatically placed on the film at a
temperature gradients as required in the test article.Auniform
rateofatleast100/sandatanaccuracyofatleast1%toverify
source of heat or cold shall be provided; that is, no “cold” or
the camera exposure rate during the impact sequence (see
“hot” spots shall be developed in the test article, and this shall
Table 1 for camera exposure rate versus impact velocity).
be verified by the use of thermocouples placed at strategic
points throughout the test article or by use of infrared (pho-
6. Materials
tography) thermographs.
6.1 Bird:
5.3.2 Enclose the mounted test article and circulate precon-
ditionedairwithinthisenclosure,stabilizethetestarticleatthe 6.1.1 The bird combined with the packaging forms the
desired test temperature, and remove the enclosure immedi- projectile that impacts the test article. If a real carcass is
atelybeforetheimpacttest.Acoolant,carbondioxideorliquid selected,itmaybeeitheradomesticorwildbirddependingon
nitrogen, may be mixed with the air to cool the air below the required weight. The standard weight of the bird used in
ambient temperatures. Hot air, heat lamps, or energized elec- this test shall be 4 lb (1.81 kg). Use a chicken as the bird for
tricalconductivecoatingswithinthetestarticlemaybeusedto this standard weight. Either freshly kill the bird just before use
raise interior or exterior temperatures. Antiicing or defogging (within 1 h) or freeze immediately after killing for future use.
systems, or both, may also be required. Store the frozen bird at 0°F (−18°C) or lower for no more than
F330–89 (2004)
TABLE 1 Camera Exposure Rate Versus Bird Impact Velocity
continue past the stripper are not considered to be significantly
V detrimental to the test article as observed in rapid sequence
F
photographic records.
Bird Impact Velocity
6.4 Crew Simulation—Manikins, modeling clay, styrofoam
Exposure Rate
ft/s m/s
(Frames/Second)
witness plates, or other flight crew representation devices may
100 30.5 1500
be used to record impact effects on the crew.
200 61.0 2000
6.5 Coolant:
300 91.4 2500
400 122.0 3000
6.5.1 Carbon Dioxide and Liquid Nitrogen—For introduc-
500 152.0 3500
tion to preconditioning air for temperature control. Caution
600 183.0 4000
700 213.0 4500 should be exercised when using these materials. See 1.3.
800 244.0 5000
900 274.0 5500
7. Transparency and Supporting Structure Test Article
1000 305.0 6000
1100 335.0 6500
7.1 Unless otherwise specified, the transparencies and sup-
1200 366.0 7000
porting structure described as the test article shall be produc-
tion parts and assemblies. Mount the transparency at the angle
of incidence in a production structure restrained at design
30 days. Thaw a frozen bird carcass at normal room tempera-
levels of rigidity. Install aircraft quality fasteners with appro-
ture for approximately 24 h (for a 4-lb bird) before use and the
priate aircraft installation procedures. The test range shall
minimum internal body temperature shall be 60°F (15.5°C) at
contain firm tie-down points for mounting the test articles.
the time of use.
6.1.2 Weighthebirdjustbeforeuse.Toachievetherequired
...
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