ASTM F330-89(1999)

Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures

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 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.  
1.3 The values stated in inch-pound units are to be regarded as the standard. The values given in parentheses are for information only.

General Information

• Status: Historical
• Publication Date: 09-Dec-1999
• ICS: 49.045 - Structure and structure elements
• Technical Committee: F07 - Aerospace and Aircraft
• Drafting Committee: F07.08 - Transparent Enclosures and Materials

Relations

• Replaced By: ASTM F330-89(2004) - Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures
• Effective Date: 01-Oct-2004
• Referred By: ASTM F790-23 - Standard Guide for Testing Materials for Aerospace Plastic Transparent Enclosures
• Effective Date: 10-Dec-1999

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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.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: F 330 – 89 (Reapproved 1999)
Standard Test Method for
Bird Impact Testing of Aerospace Transparent Enclosures
This standard is issued under the fixed designation F 330; 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.
This standard has been approved for use by agencies of the Department of Defense.
1. Scope 3.2 The specific parameters described by this method are:
3.2.1 Bird weight and condition,
1.1 This test method covers conducting bird impact tests
3.2.2 Bird velocity, and
under a standard set of conditions by firing a packaged bird at
3.2.3 Instrumentation.
a stationary transparency mounted in a support structure.
1.2 This standard does not purport to address all of the
4. Significance and Use
safety concerns, if any, associated with its use. It is the
4.1 This method may be used for: bird impact testing of
responsibility of the user of this standard to establish appro-
aircraft crew compartment transparencies and supporting struc-
priate safety and health practices and determine the applica-
ture to verify the design; compilation of test data for use in
bility of regulatory limitations prior to use. For specific hazard
verification of future transparency and supporting structure
statements, see Section 8.
design and analytical methods; and comparative evaluation of
1.3 The values stated in inch-pound units are to be regarded
materials.
as the standard. The values given in parentheses are for
information only.
5. Apparatus
2. Terminology 5.1 Gun, compressed gas, conforming in principle to Fig. 1,
comprising:
2.1 Definitions:
5.1.1 Pressure Tank, of capacity and working pressure as
2.1.1 bird—the carcass that is used to impact the test article.
discussed in Note 1.
2.1.2 bird package—the bird and container that encases the
bird to prevent disintegration enroute to target.
NOTE 1—A gun capable of propelling a 4-lb (1.81-kg) bird in excess of
2.1.3 gun—the device that propels the bird toward 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
target.
working pressure of 250 psi (1.725 3 10 Pa).
2.1.4 sabot—the container that is used to adapt the bird
package to the gun barrel. 5.1.2 Release Mechanism, comprised of a firing solenoid,
2.1.5 stripper—the device that stops the sabot at the end of
diaphragm, and a cutter. Upon initiation of the firing sequence,
the gun barrel so that only the bird and package exits from the the release mechanism allows the compressed gas stored in the
barrel.
pressure tank to flow rapidly into the gun barrel and propel the
2.1.6 test article—the transparency and supporting struc- projectile.
ture.
NOTE 2—The most common designs normally use either one or two
diaphragms in the release mechanism. In the single diaphragm design, the
3. Summary of Test Method
diaphragm is mechanically ruptured upon firing (see Fig. 1). In the dual
3.1 The method employs a smooth-bore bird gun that fires a
diaphragm system, pressurized gas between the two pressurized gas
chicken carcass so that it impacts a stationary aerospace diaphragms is bled to initiate firing by allowing the stored gas to burst
each diaphragm in rapid succession.
transparency mounted in a supporting structure.
5.1.3 Barrel (Launch Tube), a smooth bore tube that guides
the packaged bird (and sabot if used) during its acceleration by
This method is under the jurisdiction of ASTM Committee F-7 on Aerospace
the expanding air from the pressure tank. The bore and length
and Aircraft and is the direct responsibility of Subcommittee F07.08 on Transparent
of the barrel is chosen both to accommodate the largest of the
Enclosures and Materials.
projectiles to be used and for the overall performance require-
Current edition approved Feb. 24, 1989. Published May 1989. Originally
published as F 330 – 79. Last previous edition F 330 – 79. ments of the gun.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
F 330
FIG. 1 Representative Air Gun
5.1.4 Sabot Stripper may be mounted at the end of the ambient temperatures. Hot air, heat lamps, or energized elec-
launcher tube. The purpose of the sabot stripper is to arrest or trical conductive coatings within the test article may be used to
deflect the sabot, allowing only the packaged bird to impact the raise interior or exterior temperatures. Antiicing or defogging
test article. systems, or both, may also be required.
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).
by small stray objects that may be traveling with the projectile,
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, accuracy of ⁄4° (0.004 36 radian).
which are triggered by the projectiles breakage of a mechanical
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%.
5.4.5 Rapid Sequence, at least one high-speed camera shall
NOTE 3—When using a light beam measuring system under high-
be used to provide records of the bird impacting the target. The
humidity conditions, it is possible that the bird can become enveloped in
camera lighting conditions and controlling instrumentation
a cloud of water droplets that could cause triggering of the light beams and
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 5 1000 1 5 V or (1)
5.3 Environmental Control:
5.3.1 The environmental control apparatus may be used to
F 5 1000 1 1.53 v (2)
heat or cool the test article to the desired temperature at the
time of impact. The environmental control required shall be
where:
capable of providing the temperature range surrounding the test
F = exposure rate (frames per second),
article that would critically affect the physical properties of
V = projectile velocity (ft/s), and
aircraft transparencies. This range is normally −65°F (−54°C)
v = projectile velocity (m/s)
to 250°F (121°C). The facility shall be capable of providing
Timing marks may be automatically placed on the film at a
these temperatures for a sufficient time to achieve steady-state
rate of at least 100/s and at an accuracy of at least 1 % to verify
temperature gradients as required in the test article. A uniform
the camera exposure rate during the impact sequence (see
source of heat or cold shall be provided; that is, no “cold” or
Table 1 for camera exposure rate versus impact velocity).
“hot” spots shall be developed in the test article, and this shall
be verified by the use of thermocouples placed at strategic
6. Materials
points throughout the test article or by use of infrared (pho-
6.1 Bird:
tography) thermographs.
5.3.2 Enclose the mounted test article and circulate precon- 6.1.1 The bird combined with the packaging forms the
ditioned air within this enclosure, stabilize the test article at the projectile that impacts the test article. If a real carcass is
desired test temperature, and remove the enclosure immedi- selected, it may be either a domestic or wild bird depending on
ately before the impact test. A coolant, carbon dioxide or liquid the required weight. The standard weight of the bird used in
nitrogen, may be mixed with the air to cool the air below this test shall be 4 lb (1.81 kg). Use a chicken as the bird for
F 330
TABLE 1 Camera Exposure Rate Versus Bird Impact Velocity
stripper combination shall be designed so that either all of the
V sabot is arrested by the stripper or the fragments of sabot which
F
continue past the stripper are not considered to be significantly
Bird Impact Velocity
detrimental to the test article as observed in rapid sequence
Exposure Rate
ft/s m/s
(Frames/Second) photographic records.
100 30.5 1500 6.4 Crew Simulation—Manikins, modeling clay, styrofoam
200 61.0 2000
witness plates, or other flight crew representation devices may
300 91.4 2500
be used to record impact effects on the crew.
400 122.0 3000
500 152.0 3500 6.5 Coolant:
600 183.0 4000
6.5.1 Carbon Dioxide and Liquid Nitrogen—For introduc-
700 213.0 4500
tion to preconditioning air for temperature control. Caution
800 244.0 5000
900 274.0 5500
should be exercised when using these materials. See 1.2.
1000 305.0 6000
1100 335.0 6500
7. Transparency and Supporting Structure Test Article
1200 366.0 7000
7.1 Unless otherwise specified, the transparencies and sup-
porting structure described as the test article shall be produc-
this standard weight. Either freshly kill the bird just before use
tion parts and assemblies. Mount the transparency at the angle
(within 1 h) or freeze immediately after killing for future use.
of incidence in a production structure restrained at design
Store the frozen bird at 0°F (−18°C) or lower for no more than
levels of rigidity. Install aircraft quality fasteners with appro-
30 days. Thaw a frozen bird carcass at normal room tempera-
priate aircraft installation procedures. The test range shall
ture for approximately 24 h (for a 4-lb bird) before use and the
contain firm tie-down points for mounting the test articles.
minimum internal body temperature shall be
...